1
10
47
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/10242/whyinternalinsulationforthesaturns-iv_041207133311.pdf
18f85aa277d21fd5e2e09ddc9c1674db
Dublin Core
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Title
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Saturn V Collection
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
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Saturn V Collection
Description
An account of the resource
<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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whyinternalinsulationforthesaturns-iv_041207133311.pdf
spc_stnv_000940
Title
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"Why internal insulation for the Saturn S-IV liquid hydrogen tank?."
Description
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Prepared for presentation at the Cryogenic Engineering Conference, Los Angeles, California, August 14-16, 1962.; There is no page 8.
Creator
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Herstine, Glen L.
Date
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8/14/1962
Temporal Coverage
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1960-1969
Subject
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Saturn project
Liquid propellant rockets
Propellant tanks
Fuel tanks--Linings
Saturn S-4 stage
Type
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Text
Presentations
Source
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Saturn V Collection
Box 7, Folder 23
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
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spc_stnv_000925_000942
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http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17255
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/2328/spc_stnv_000100.pdf
0bb3df04da742c1b6310fc584bdc94e9
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Title
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Saturn V Collection
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
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Saturn V Collection
Description
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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Identifier
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spc_stnv_000100
Title
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"Apollo Vehicle Propulsion Systems."
Description
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This paper discusses the propulsion requirements for various stages of the Apollo vehicles and the development of these engines.
Creator
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Belew, Leland F.
Patterson, Wayne H.
Thomas Jr., James W.
Date
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1965-07
Subject
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Apollo project
Liquid propellant rocket engines
Liquid propellant rockets
Project Apollo (U.S.)
Saturn Project (U.S.)
Space vehicles--Propulsion systems
Spacecraft propulsion
Source
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Saturn V Collection
Box 14, Folder 35
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
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spc_stnv_000075_000118
Is Referenced By
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http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17182
Alternative Title
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AIAA Paper No. 65-303.
Temporal Coverage
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1960-1969
Type
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Reports
Still Image
Text
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/2318/spc_stnv_000090.pdf
7a0ab6bc600778855b7a1bcda81f98c4
Dublin Core
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Title
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Saturn V Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
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Saturn V Collection
Description
An account of the resource
<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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Identifier
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spc_stnv_000090
Title
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Telegraphic message containing an Apollo Program Flash Report.
Description
An account of the resource
This message for the Apollo Program Director contains a report of the Apollo launch vehicles, problem that occurred, and actions required. The photocopy is difficult to read.
Creator
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Belew, Leland.
Date
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1965-07-09
Subject
The topic of the resource
F-1 rocket engine
Liquid propellant rockets
Project Apollo (U.S.)
Saturn Project (U.S.)
Saturn launch vehicles
Saturn S-1C stage
Source
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Saturn V Collection
Box 14, Folder 27
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
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spc_stnv_000075_000118
Is Referenced By
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http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17174
Temporal Coverage
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1960-1969
Type
The nature or genre of the resource
Telegraphs
Text
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/2317/spc_stnv_000089.pdf
20a2514cf0bae1857c0a1420d6882f3e
Dublin Core
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Title
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Saturn V Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
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Saturn V Collection
Description
An account of the resource
<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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Identifier
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spc_stnv_000089
Title
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Telegraphic message containing an Apollo Program Flash Report.
Description
An account of the resource
This message for the Apollo Program Director contains a report of the Apollo launch vehicles, problem that occurred, and actions required. The photocopy is difficult to read.
Creator
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Belew, Leland F.
Date
A point or period of time associated with an event in the lifecycle of the resource
1965-07-01
Subject
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Saturn Project (U.S.) F-1 rocket engine
Liquid propellant rockets
Project Apollo (U.S.)
Saturn launch vehicles
Saturn Project (U.S.)
Saturn S-1C stage
Source
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Saturn V Collection
Box 14, Folder 27
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
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spc_stnv_000075_000118
Is Referenced By
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http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17174
Temporal Coverage
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1960-1969
Type
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Telegraphs
Text
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/995/spc_stnv_000048.pdf
6c86756dd61d4b98b584d3f3d947da52
PDF Text
Text
Tho Aorojot propoonl for a 1,000,000 pound tilruoe hydrogon oxygen
engIno is for e cooiglctely new mgLnr.. l71oy claim that t h e i r d e s i ~ n
utilizes to t h e f u l l e o t extent p o o s i b l e praneilt otcate-of-the-art
and currently w e d techniques. Tiley have already s tnrtetl design arudiee
and 61i)all 0ca1e d~weI-opcwneo f sob= ol tba crnpvnellts mine company
Punde
-
.
They e a t i n a c e that 24 munttie acter rlic c o n t r a c t ie let the c n ~ i n ewill
be r ~ u ~ lfor
y PCRT. D e l i v e r y o f the f i r o t ground tent engine i o estirxited
18 alonthn a f t e r the contract l o ~ i m n l c d . T i ~ i ais a m w i ~ a t optinis
.
i n cmlpnrioon to our rilanntd lunnr lntldioa otucly results wi~orefnwe
e s t i m a t e d 36 rnontho to PFXT t e o t n aid 30 n o n t h o to delivery6& t h e firtat
ground t e a t @n,7ineo. S m oi' this 12 wont113 d I f L e r e n c ~m y & be
explnjned by t h e pre-cootmct work currently under way a t Acrofet.
\ .
The F - l engine a o ouch cannot Go adapted t o hydro-en o;cy;en p r e
pcflnats. To adapt the F-1 engine to h y d r o ~ c no q g e n would require o
mjor redcsian oB e c s c n t i a l l y a l l oE tlis engine crn?oncnts which i n
easence reaulte in a now e . ~ g i n s .
�
Dublin Core
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Title
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Saturn V Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
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Saturn V Collection
Description
An account of the resource
<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
Dublin Core
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spc_stnv_000048
Title
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Memo from William A. Fleming to Robert Seamans concerning an "Aerojet proposal for 1,000,000 pound thrust hydrogen oxygen engine."
Creator
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Fleming, William A.
Seamans, Robert C.
United States. National Aeronautics and Space Administration
Date
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1961-07-27
Temporal Coverage
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1960-1969
Subject
The topic of the resource
Liquid propellant rockets
Saturn Project (U.S.)
Hydrogen oxygen engines
Saturn 5 launch vehicles
Type
The nature or genre of the resource
Correspondence
Text
Source
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Saturn V Collection
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Is Part Of
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NASA HQ Miscellaneous Correspondence August 1968
Language
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en
Rights
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
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spc_stnv_000027_000050
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/983/spc_stnv_000036.pdf
6eb3c8813129aea297f81174b1a84f4f
PDF Text
Text
rnANCES
IN PIWrnG TErnOLOGY
AM) ROCKET
EXGI?ii TlTRBOmMP APPLICATIONS
C h m l e s A. MacGregor
Supervie or
Advanced Turbomachinery
D~~~
---------- Doc. No. --------
Rocke tdyne
A D i v i s i o n of Korth American A v i a t i o n , Inc.
Canoga Park, C a l i f o r n i a
Royce Hall, Roam
a p a r t o f t h e NASA-
on t h e Transformat i o n of Knowledge and I t s U t i l i z a t i o n .
�rnT1LYcES
m
PUMPING TECHNOLOGY AND R O m
E
N
G
m TURBOPUMP APPLICATIONS
Charles A. MacGregor
Superv ie o r
Advanced Turbomachinery
Bocke tdgne
A Division of North American Aviation, Ina.
Canoga Park, C a l i f omia
INTRODUCTION
This r e p o r t i s divided i n t o two general p a r t a .
The f i r s t p a r t ir a
d e s c r i p t i o n 6f turbopumps f o r l i q u i d r o c k e t enginee m they e x i s t today.
For campletenesa and understanding, same background i a f o r m a t i a a is
included on why turbopumps have evolved t o t h e i r preeent configarationm.
The second p a r t suggest portion8 of t h i s e f f o r t t h a t may have some
a p p l i c a b i l i t y t o t h e general ecanomy.
TURBOPUMP FOR LIQUID BOCIiET E N G I N S
The turbopump hae t h e d i e t i n c t i o n of being one of t h e moat im,partmt
Its f u n c t i o n in an engine h t s l l a t i o n i s t o receive propellante from t h e tanka and d e l i v e r them t o tha
components in a l i q u i d rocket engine.
�t h r u s t chamber a t design pressure l e v e l s and f l o w r a t e s s o t h a t the engine
can develop deaign t h r u s t a t the required chamber pressure.
.
The turbopump
i s r o t a t i n g machinery assembly , which cone ia t s of a 'pump ( o r pumps) for
i n c r e a s i n g the pressure l e v e l of the propellant(s).
The power t o d r i v e
'the p ~ p ( s i)n t h i s assembly is aupplied by a t u r b i n e , which u t i l i z e .
working f l u i d s supplied by the engine system gas generator.
Tut%opump
design configurations can vary depending on t h e engine combustion p r o c e r r ,
t h e i n s t a l l a t i o n requirements, and the p r o p e l l a n t s being pumped.
Detailed
d e e c r i p t i o n s of turbopump configurations w i l l be presented in the following
text.
F l u i d s and F l u i d P r o p e r t i e s
The major f a c t o r influencing the t ~ p eof turbopump d e s i g n chosen for any
a p p l i c a t i o n is the d e n a i t y of the propellants t o be pumped.
Variaticmm
i n o x i d i z e r and f u e l d e n s i t y requires the i n d i v i d u a l pumps t o be operated
a t speeds capable of obtaining respective pump head and volume flows.
A
t a b u l a t i o n of p r o p e l l a n t p r o p e r t i e s , which shows t h e v a r i a t i o n in propell a n t d e n s i t i e s , appear.
in Table 1
.
For turbopumps pumping p r o p e l l a n t combineti o m t h a t have s i m i l a r d e n s i t i e r ,
both pumps can be run a t the same speed.
In cases where a g r e a t v a r i a t i o n
i n p r o p e l l a n t d e n s i t y e x i s t s between the oxidizer and f u e l , an i n the
l i q u i d oxygen ( ~ O X ) / l i ~ u i hydrogen
d
(5)
cmbination,
each pump i a
driven at i t s b e s t design speed t o most e f f i c i e n t l y meet i n d i v i d u a l
head requirementr
.
�Data a t NormalTemperature,
Liquid
*2*1
60
Vapor
Pressure,
psia
11.1
Density,
lb/cu it
Viscosity
~107.
lb-scc/sq in.
90.88
0.657
60
0.152
63.25
1-49
60
0 255
62.37
1-65
RP- 1
60
0.01
50.45
5-51
EthylAlcohol
(95 percent5 percent)
60
0.652
50.44
2.247
UDMH
60
1.89
49.71
0.815
UX*
-297.5
14.6
71.39
0.277
llFL
-305
16.0
93.77
0
W2
-315
20.70
49.50
NX
N2H4
H2°
J
F
Conditions
A
338
0 ,0206
-425
4.42*
10.62
I=2
*Density a t 14.7 psi.
+wXormal conditions do n o t necessarily imply standard conditionr, i f
tank pressures have been applied.
A
�Operating Rauge
Figure 1
i s a p l o t showing t h e range of o p e r a t i o n f o r t y p i c a l p r o p e l l a n t
pumps i n terms of pump head and flow.
This curve demonstrates how t h e
head requirements f o r t h e l e s s dense p r o p e l l a n t , l i q u i d hydrogen, are much '
The p l o t
g r e a t e r t h a n t h o s e r e q u i r e d by e i t h e r l i q u i d oxygen o r RP-1.
shown in F i g . 2
i s t h e o p e r a t i o n envelope of c u r r e n t turbopump t u r b i n e
d e s i g n s based on power and speed requirements.
Turbine working f l u i d
mass f l o w r a t e depends on the p r o p e r t i e s of t h e s e f l u i d s , t h e power
#
development r e q u i r e m e n t s , amount of energy from t h e s e f l u i d s made a v a i l a b l e t o t h e t u r b i n e t o c o n v e r t i n t o work, and t h e t u r b i n e d e s i g n and
t p e r a t i n g parameters.
A l i s t of working f l u i d p r o p e r t i e s f o r canmon
p r o p e l l a n t combinations appears i n T a b l e 2.
As power requirement8
f o r a s p e c i f i c d e s i g n o p e r a t i n g p o i n t i n c r e a s e , t h e r a t i o of t u r b i n e maar
f l o w r a t e t o Cngine flow i n c r e a s e s .
I f chamber p r e s s u r e is i n c r e a s e d f o r
a f i x e d thrust c o n d i t i o n , t h e t u r b i n e power requirements t o d e v e l o p t h e
needed pump heads become g r e a t e r .
A p l o t of t u r b i n e t o engine weight
flow r a t i o v s chamber p r e s a u r e , f o r a gas g e n e r a t o r i n s t a l l a t i o n , i s shown
in F i g .
3.
.
The curves f o r b o t h LOX/RP-1
and LOX!LH~ c l e a r l y shmr t h a t ,
as d e s i g n chamber p r e s s u r e i s i n c r e a s e d , t h e t u r b i n e t o engirie weight f l o v
r a t i o i n c r e a s i n g l y i n f l u e n c e s engine performance.
The e f f e c t of chamber
p r e s s u r e on turbopump weight i s a l s o an important d e s i g n c o n s i d e r a t i o n ;
t o meet t h e i n c r e a s e d power requirements f o r h i g h e r chamber p r e e s u r e a ,
t h e turbopump assembly weight becomes h e a v i e r .
A p l o t ahowing t h e
e f f e c t of chamber p r e s s u r e on t h e turbopump t o e n g i n e weight r a t i o i.
s h a m in Fig. 4.
���TABLE 2
PROPERTIES
Inlet'
Temperature,
Fluid
IAX/RP- 1
N20 4 / ~ ~ 3
(-1
lox/%
L
F
Y
ft lb/lb F
Mixture
Ratio,
o/f
1.097
1.100
43.3
45.1
0.93
0.320
1.106
47.1
0.337
C
P'
~ t u / l bF
n,
1100
0 635
1150
1200
0.639
0.643
1250
0.646
1.111
58.6
0 354
1300
0.648
50.4
0.372
1350
1400
0.651
1.115
1.119
51.8
0.390
0 653
1.124
53.6
0.408
1450
0 655
1.128
0.425
1500
0 657
1.132
55-4
58.0
1550
1600
0.659
0.660
1.137
59.0
0.460
1.140
60 7
0.478
1650
0.661
1.144
62.4
1700
0.662
1.148
64.0
0,497
0,516
1400
0.380
1.42
0.11
1500
1.42
1600
0.398
0.416
87.5
91.6
1.42
95.7
0.22
1700
0.434
1.42
99.9
0,274
1800
0.452
1.42
104.0
0.328
1900
0.470
1.42
108.2
0.382
1000
2.05
1.374
434
0.785
1200
1.94
1.364
403
0
1400
1.86
1.354
378
1.025;
1600
1.80
1 343
358
1. ir3
1800
1.73
1.69
1 333
1.322
3%
1.273
320
1.410
2000
0.443
0.165
903
.
���TURBOPUMP DESIGN PROCESS
3
The process of designing a turboppp is shown graphically in Fig. 5.
The influence of the various quantities that must be considered and
determined are shown so that the turboplmp can be specified graphically
and analytically. It is through this process and by considering these
items that the various turbopump designs have evolved.
Turbopump Design Criteria
In selecting a turbopump design geometry, it is necessary to have a set
of criteria by whihh to establish the desirability of a configuration.
The criteria used for this selection are classified as keliabjlity,
flexibility, ease of development, weight, and performance.
The most important single criterion is that of turbopump reliability;
it defines the expected successful performance of the turbopump in meeting
the requirements of the design. Experience has shown that good reliability
is a function of using design principles and techniques that are simple
and provide a sound basis for performing the mechanical function for which
at is designed. In addition to simplicity of design, the reliability
of a machine depends on utilizing as few detail parts aa necessary t o
perform the job intended by the design.
A turbopump design must incorporate the characterietic of flexibility
toward operating under a wide variety of conditions.
This flexibility
must include thie ability t o deviate from the design operating point,
eaae of the unit to prwide a base from which it can be uprated to prwida
a higher level of performance, and also the provision of changing individual
pump operating points to facilitate adjustments in engine mixture r a t i o .
,
�+
I
THRUST SlZE PROPELLANTS IMR)
CHAMBER PRESSURE
I
APPLICATION
ENGINE DESIGN POINT
EQUIVALENT WGT
ENGINE CYCLE
T/C COOLING METHOO
I
d
T/P DESIGN POINT
1
+
POWER TURBINE INLET. O~SCH AND
WORKING FLUID CONDITIONS
T/P INSTALLATION
T/P MOUNTING
GIMBALLING
DUCT SIZES
DUCT LOADS (FLEX JOINTS)
J
1
I
THROTTLING RANGE
W REOUIREMENTS
STARTING METHOD
RESTARTING REOUIREMENT
CALIBRATION AND DESIGN
POINT DEVIATIONS
L
STATE-OF-THE-ART
LIMITATIONS
64
L
b
+
I
I
DESIGN PROBLEMS
FLOW STABILITY
COMPONENT EFFICIENCY
AXIAL AND RADIAL FORCES
TEMPERATURE GRADENTS
TORQUE TRANSMlSS#HI
CRITKAL SPEED
FABRICATKN( PROCESSES
MATERIAL SELECTION
STATK DEFLECTKH(S
WORKING STRESS LEVELS
H K ~ N PRESSURE FLANGE
A
OFF-DESIGN REQUIREMENTS
RELIABILITY
FLEXIBILITY
DEVELOPMENT
*
.
CAVITATION
BEARINGS
TIP SPEEDS
SEAL LIMITS
STAGE LOADINGS
T/P CONFIGdRATlON
PUMP TYPE AND SIZE
TURBINE TYPE AND SIZE
k
+
T/P DESIGN
LAYOUT
WEIGHT
T/P PERFORMANCE
OEVELOPMENT EFFORT
h
Figure 5.
Turbomachinery Design Process
�The c r i t e r i a t h a t provide f o r e a s e of a e - ~ r l o p i n e n tf o r a turbopump
c o n f i g u r a t i o n a r e of major importance.
2 e s e include t h e o r g a n i z a t i o n t r
experience and a b i l i t y t o f a b r i c a t e and s ~ c c e s s f u l l yt e s t a new t u r b o pump d e s i g n , t h e e x i s t e n c e of knowledge r s p e r f o m t h e program, and
a b i l i t y t o p r e d i c t t h e magnitude and time of t h e development program.
Another important c o n s i d e r a t i o n a f f e c t -
e a s e of development is t h e
a b i l i t y t o p r e d i c t performance; t h i s c a p e 5 i l i t y p r o v i d e s f o r a p r o t o t y p e
d e s i g n t h a t r e q u i r e s a minimum of m o d i f i c e t i o n s and o b t a i m t h e d e e i r e d
program o b j e c t i v e s i n a s h o r t e r d e v e l o p n c n t time period.
The p r e d i c t i o n of turbopump d r y weight
FS.~
performance can be combined
I
in terms of e q u i v a l e n t weight, i. e . , t h e rurbopump dry w e i g h t i s added
t o t h e weight r e p r e s e n t i n g t h e e q u i v a l e n z p r o p e l l a n t weight conaumed b y
t h e turbopump, expressed in terms of i n i r i a l m i s s i l e payload w e i g h t .
This c r i t e r i a i s t h e l e a s t d i f f i c u l t t o i r e d i c t a n a l y t i c a l l y f o r a new
design application.
Turbopump D e s i Requirements
~
To s a t i s f a c t o r i l y meet t h e requirements c f a s p e c i f i c e n g i n e a p p l i c a t i o n ,
t h e turbopumps in many of t h e new engine c',esigns, i n a d d i t i o n t o o p e r a t i n g
a t s t e a d y - s t a t e c o n d i t i o n s , must have t h e c a p a b i l i t y of t h r o t t l i n g e n g i n e
t h r u s t t o meet s p e c i f i c mission r e q u i r e c e 3 t s .
t h e f l e x i b i l i t y t o be used w i t h differer;:
The d e s i g n a l s o mst have
engine s t a r t i n g methods; t h i r
can v a r y from uee of p r o p e l l a n t tank head t o start t h e pumping of p r o p e l l a n t s t o t h e t h r u s t chamber, o r perhaps a t u r b i n e s p i n start from an
auxiliary power source.
With any start nequence, t h e pumps m e t smoothly
develop r e q u i r e d heads and f l w e w i t h o u t c a v i t a t i n g o r transmitting
p r e s e u r e p u l s e e through t h e p r o p e l l a n t s z p p l y eyetem.
Additional
�requirements that may be imposed on a turbopump are those of providing
engine restarts in flight, or varying engine mixture ratio in flight
operation so that all the propellants in the tanks can be utilized during
the flight mission.
Design Problems and Solutione
Turbopump experience has shown that there are baeic design problem which
must be considered and solved before a new configuration will eatisfactorily
meet required operating specificatio~.
The individual pumps will be required to demonstrate stable performance
characteristics for the full operating range of the turbopump without
having tendencies of cavitating, transmittiag pressure pulses to the
propellant feed aptem, or going into a region of stall. Development
tests are conducted with both air and water, using pump detail inducers,
impellers, and puxp subassemblies at a pump component test facility to
ascertain that the pumps will perform satisfactorily before being used in
a turbopump assembly. Comparable tests are conducted with the turbine a b
a turbine test facility.
\
Attaining the individual efficiencies of components used in the turbopump
can. be a trouble source in qualifying a new turbopump design.
To emure
that the units are operating at required performance levels, all components
are fully developed for the full range of operation in component test
facilities prior to their use ae turbopump production configurations.
Loads arising from axial and radial forces can reach proportions capable
of causing internal damage because of rubbing of rotating parts; in
.
�extreme cases, complete failure of the turbopump by explosion can be
experienced if the propellant being pumped has the properties of liquid
oxygen. To eliminate auc= problems, the pumps are designed with balance
pistons, and with provisioas to evenly distribute pressures within the
pumps. The work with be&-ings capable of withstanding larger radial
and axial loads is aimed st helping to minimize this type of problelh.
Considerable work has bee3 done to eliminate problems caused by temperature grediente within the pump. With a cryogenic turbopump deaign, it is
possible to have a pump c2eratin.g at a temperature less than -300 to 400 F
mounted adjacent to a tur3ine operating with working fluid temperatures
ranging from 1200 to 170C F. This environment and temperature gradient
presents problem with differential contraction and expansion, lubrication, and sealing. Cryogeaic turbopump design and development experience
has established techniques for cooling and allowing far thermal growth
between adjacent components.
Problems associated with fabrication processes for new turbopump design
configurations are dealt with by two approaches. Primary considerations
are given to the design of a component to establish if the complexity of
the unit could be simplified and still perf o m in the same manner. If
the design is committed t o fabrication, the individual casting, forging,
and machining processes a=d techniques are improved or developed so that
parts can be produced with consistent quality.
In some difficult instances,
either the mode of fabrication or material is changed. Casting processes
for new pump volutes are often developed so that the volute casting will
be of acceptable quality.
Experience with selecting materials for fabricating new turbopump hardware
has shown that newly developed alloy8 with propertiee suitable far turbopump service often preeent machining problems.
In most cases, all much
�problems were e l i m i n a t e d as machining experience w i t h t h e new a l l o y
was accumulated.
h l e n s e l e c t i n g m a t e r i a l s f o r f a b r i c a t i n g a new component,
those comon m a t e r i a l a t h a t have been worked w i t h p r e v i o u s l y a r e i n v e s t i g a t e d f i r s t , r a t h e r than u s i n g a new e x o t i c type w i t h p r o p e r t i e 8 t h a t far
exceed t h e maximum requirements f o r t h e a p p l i c a t i o n .
There have been i n s t a n c e s when problems a s s o c i a t e d w i t h t o r q u e t r a n s m i a s i o n
and c r i t i c a l speed have had t o be s o l v e d i n turbopump development programs.
On& method of minimizing t h e problems of t r a n s m i t t i n g t o r q u e ( f o r example,
frum t h e t u r b i n e t o t h e pumps)has been t o u t i l i z e c u r v i c c o u p l i n g s in t h e
designs.
They have proved v e r y s a t i s f a c t o r y in s e r v i c e .
In c h e c k i n g new
turbopump d e s i g n s , t h e c r i t i c a l epeed i n bending i s analyzed f o r the
r o t a t i n g assembly.
For d e s i g n s t h a t o p e r a t e above t h e f i r e t c r i t i c a l , t h e
c a l c u l a t e d f i r e t c r i t i c a l should be no more than 85 p e r c e n t of t h e d e e i p
speed.
For t h e c a s e of o p e r a t i o n below t o e f i r s t c r i t i c a l , the c a l c u l a t e d
f i r s t c r i t i c a l should be no l e s s t h a n 150 p e r c e n t if t h e d e s i g n epeed.
Turbopump s t a t e - o f - t h e - a r t
l i m i t a t i o n s r e p r e s e n t t h e e x i s t i n g boundaries
t o man's knowledge concerning turbopumps.
Exceeding any one of t h e s e
l i m i t a t i o n s w i l l r e s u l t i n a turbopump t h a t i e e i t h e r u n r e l i a b l e o r
inefficient.
Rocket engine turbopumps a r e designed a t t h e maximum a l l o w a b l e r o t a t i o n a l
epeed because of weight c o n s i d e r a t i o n s .
Figure 6
demonstrates t h i r
r e l a t i o m h i p between turbopump weight and r o t a t i o n a l apeed.
'
��Each s t a g e cf a r o c k e t engine pump d e i i v e r s a s much work as t h o
s t r u c t u r a l a d hydrodynamic l i m i t a t i o n s w i l l a l l o w , because t h e number
of r e q u i r e d s t a g e s i s i n v e r s e l y p r o p o r t i o n a l t o t h e work d e l i v e r e d per
stage.
This minimizes t h e pump w e i g h t , because pump weight ' i n c r e a s e r
w i t % t h e number of r e q u i r e d s t a g e s .
The f o l l o w i n g hydrodynamic and s t r u c t u r a l phenomena p l a c e an upper limit
on r o t a t i o n a l speed and a lower l i m i t on t h e number of pump s t a g e e .
Cavitation .
C a v i t a t i o n w i t h i n a pump i s t h e passage of t h e pump flow from t h e l i q u i d
phase t o t h e v a p o r phase.
This s e v e r e l y r e s t r i c t s t h e weight flow d e l i v e r e d
by t h e pump, because of two i n t e r a c t i n g r e a s o n s :
(1) t h e volume f l o w r a t e
d e l i v e r e d by a pump is c o n s t a n t , and (2) a vapor occupies a much l a r g e r
volume t h a n t h e c o r r e s p o n d i n g l i q u i d .
C a v i t a t i o n a l s o w i l l cause s e v e r e
e r o s i o n of t h e flow passages i n a pump t h a t o p e r a t e s f o r l o n g p e r i o d s of
time, because t h e v a p o r c a v i t y c o l l a p s e s v i o l e n t l y when it p a s s e s i n t o a
higher pressure region.
This e r o s i o n i s a minor c o n s i d e r a t i o n i n r o c k e t
engine pumps, because t h e s e pumps have a v e r y s h o r t o p e r a t i n g d u r a t i o n .
These a d v e r s e e f f e c t s of c a v i t a t i o n a r e minimized by a t t a c h i n g an i n d u c e r
upstream of t h e main i m p e l l e r i n l e t .
This inducer r a i s e s t h e p r e s s u r e of
t h e pump f l o w t o a l e v e l a t which t h e f l a w w i l l n o t c a v i t a t e w i t h i n the
impeller.
I
I
I
�An inducer will operate satisfactorily rrt low pressures because it
is designed to avoid low-pressure regions within the flaw passing through
it. Figure 7 is a photograph of a typical inducer. It is a small
axial stage with a large inlet area and a small number of vexy thin,
low-cambered blades. This type of design avoids low-presaure regiom by
minimizing the relative velocity of the f l m as it passes over the blader.
Bearings
The speed limit of rolling contact bearings is expressed by the parameter
DN. This parameter is directly proportional to the tangential velocity
of the shaft OD, and is the product of the diameter (in millimeters) of
the shaft that passes through the bearing, and the shaft rotational speed
=pap-
Depending on the lubricant, the DN limit for rolling contact bearings im
in excess of one million (I'ig. 8 ).
Operation at higher DN values will
cause contact fatigue in the outer race and excessive heat generation.
These modes of failure are caused by high centrifugal forces and nonrolling
phenomena, respectively.
Rocket engine turbopump bearings are lubricated by the propellant being
pumped. This eliminates a separate lubrication system and reduces sealing
problem. Explosions can occur if separate lubricants are used, and they
mix with the ~ropellants.
�ma-11/19/61-1
P i p e 7.
Typical Turbopump Inducer
��Seale
The f u n c t i o n of a s e a l is t o minimize or p r e v e n t t h e leakage of a c o n t a i n e d
f l u i d by p r e s e n t i n g a high r e s i a t e n c e t o flow along any p o t e n t i a l leakage
path.
This is accomplished i n r o t a t i n g machinery by mechanically f o r c i n g
t h e s e a l f a c e a g a i n s t t h e s u r f a c e of t h e r o t a t i n g element.
The v e l o c i t y a t which t h e s e a l f a c e rubs a g a i n s t t h e r o t a t i n g element
has an upper limit (depending on t h e l i q u i d being s e a l e d ) i n excees of
300 f p s ( ~ i g . 9 )
Operation a t h i g h e r v e l o c i t i e s w i l l g e n e r a t e e x c e e s i v e
h e a t , which w i l l reduce t h e c o o l i n g c a p a c i t y of t h e surrounding l i q u i d
by v a p o r i z i n g it.
The r e s u l t of such o p e r a t i o n i s a r a p i d t e m p e r a t u r e
r i s e f o l l o w e d by f a i l u r e .
Structural Limitations
The c e n t r i f u g a l s t r e s s a t t h e r o o t of t h e t u r b i n e b l a d e s can l i m i t t h e
turbopump r o t a t i o n a l speed.
This s t r e s s i s p r o p o r t i o n a l t o t h e pr8duct
of t h e m a x i m t u r b i n e annulus a r e a and t h e square of t h e speed. Theref o r e , t h e m a x i m speed allowed by t h i s l i m i t a t i o n i s s e t i f t h e t u r b i n e
f l o w r a t e , i n l e t c o n d i t i o n s , and h o r s e p m e r a r e e p e c i f i e d , becauee t h e s e
parameters s e t t h e annulus a r e a .
The amount of head r i s e p e r ahrouded c e n t r i f u g a l s t a g e i s l i m i t e d by a
maximum a l l o w a b l e t i p speed of 2200 f p s i f t h e i m p e l l e r i s made of
titanium.
Higher t i p epeeds w i l l cause y i e l d i n g in t h e i m p e l l e r , becaure
t h e c e n t r i f u g a l s t r e e s e e w i l l be exceeaive.
Unshrouded c e n t r i f u g a l
i m p e l l e r s c a n o p e r a t e a t h i g h e r t i p speeds, b u t have l m e r e f f i c i e n c i e r
and e x c e a e i v e axial f o r c e r .
��Hydrodynamic Limi t a t iona
The b l a d e s of an a x i a l pump s t a g e should t u r n t h e flow aa much as
p o s s i b l e , because t h i s maximizes t h e amount of work p u t i n t o t h e f l u i d
per stage.
This minimizes t h e pump l e n g t h by minimizing t h e number of
st a g e s .
The
The t u r n i n g i s l i m i t e d by t h e maximum allowable d i f f u s i o n f a c t o r .
r o t o r d i f f u s i o n f a c t o r is d e f i n e d a s f o l l o w s ( r e f e r r i n g t o Fig.10
):
where
The s t a t o r d i f f u s i o n f a c t o r should be e i m i l a r , because e f f i c i e n c y
c o n s i d e r a t i o n s make 50-percent r e a c t i o n a t a g i n g d e s i r a b l e .
B l a d i n g w i t h a d i f f u s i o n f a c t o r of 0.7 w i l l p e r f o m w e l l .
demonstrated by experimental t e s t i n g at Rocketdyne.
This has been
Loading i n excesa
of t h i s v a l u e , however, can r e s u l t i n low pump e f f i c i e n c y from flow
s e p a r a t i o n w i t h i n t h e b l a d e row.
D i f f u s i o n problems w i t h i n c e n t r i f u g a l i m p e l l e r s can be a l l e v i a t e d by
u s i n g backward curved vanes.
Thin w i l l reduce t h e d i f f u s i o n w i t h i n t h e
i m p e l l e r p a s s a g e , because t h e t i p r e l a t i v e v e l o c i t y w i l l have a backward t a n g e n t i a l component a s w e l l as a r a d i a l cmpontnt.
��r n W E N C E OF THE LlMITS
The i n f l u e n c e of t h e s e l i m i t s on turbopump r o t a t i o n a l speed is demonstrated
i n Fig.
11.
The s p e c i f i c speed l i m i t i n d i c a t e s t h e maximum epeed a t which
a c e n t r i f u g a l pump can be operated.
Axial pumps must be used i f thin
l i m i t a t i o n is t o be exceeded, because t h i s l i m i t a t i o n i n d i c a t e s t h a t the
t
i m p e l l e r i n l e t diameter i a almoet equal t o the impeller t i p diameter.
Seal
speed and b e a r i n g DN l i m i t s are evaluated f o r s h a f t s that a r e e i e e d by
c r i t i c a l speed c o n s i d e r a t i o n s and by t h e t o r a i o n a l s t r e e s l i m i t .
TCTRBOPWP CONFIGURATIONS
Turbopumps can be designed i n t o a number of d i f f e r e n t c o n f i g u r a t i o n s and
arrangements.
The f i n a l s e l e c t i o n depends ?n the d e e i r e d speed r a t i o
between pumps, t h e arrangement of components, and the energy source of t h e
t u r b i n e working f l u i d .
There a r e t h r e e b a s i c turbopump d e s i g n t y p e s :
1.
Geared turbopump
2.
S i n g l e - s h a f t turbopump
3.
Dual-ahaft turbopump
Geared Turbopump
The geared turbopump d e s i g n c o n f i g u r a t i o n u t i l i z e e a gear box w i t h which
t o d r i v e t h e f u e l and o x i d i z e r pump a t d i f f e r e n t epeeds w i t h a a i n g l e t u r b i n e
d r i v e aesembly.
Figure
12 containrr a cutaway photograph of a
LOX/RP-~
g e a r turbopump c o n f i g u r a t i o n t h a t i s c u r r e n t l y i n s e r v i c e i n a 150,000pound-thrust b o o e t e r engine.
�PUMP FLOW RATE
Figure 11.
- GPM
Maxhmm rotational speeds allowed by varioas limite.
�Figure 12.
Geared Twbopwp.
�Single-Shaft Turbopumg
The turbopump photographs shown in Fig. l3and 14 are of single-shaft
turbopump configurations. In this type design, both the oxidizer and
fuel pumps a r e driven on one shaft by a single turbine. The turbopump
shown in Fig.13 is for an engine rated at 70,000 pound8 thrust. The
single-shaft turbopump assembly shown in Fig. 14 is being used in LWRP-1,
1,500,000-pound-thrust engine.
Dual-Shaft Turbopump
The dual-shaft turbopump configuration utilizes separate shafts to drive
the oxidizer and fuel pump8 st the best speed to meet the head and flow
ia driven
requirement of the propellanta that are being pumped. Each p~
by its uwn turbine; pump speeds heads and flows can be adjusted independently
with this type pump installation. Dual-shaft configurations are used for
pumping propellant combinations that have large differences in density;
one such propellant combination is ~0../4.
Photos shown in Fig. 15.
and b are of dual-shaft, LOX and
turbopumps respectively, for a 200,000-
3
pound-thrust engine application. In dual-shaft installation, the turbine8
can be installed either in series or in parallel to one anothar.
�Figure 13.
S i q l e @aft'Porboprrmp Fop
P
d Thrast Engine.
70,000
�Figare 14.
Tarbopa~~g
For 130UK Tbnuf
Engine.
��TCRBOPUP DE%'I%OF?.IATSAPPLICABLE
TO TIIE GEX3XA.L ECONOMY
Items presented in this section have been developed in connection with
turbopumps and may have some applicability to the general econoqy.
The turbopump, in configuration, is simply constituted.
It ie made up of
two p m p s and a single turbine variouly mounted on a single shaft or,
in the past, a gear box has been used to transmit power from t h e turbine.
Both roller and ball bearings which will take radial and a n a l loade impoaed
on the rotating assembly have been used.
Dynamic seals are ueed at the
impeller and on the shaft to control leakage and thruet, and are placed
to prevent mixing of the propellants.
Positive static seals are need in
the stationary assembly to prevent the hazard8 of external leakage,
The remaining major components are the paup volute, turbine manifold and
the shaft, the former of b%ich must contain either high-preseure or hightemperature fluid within a sound structure, and the latter must transmit
torque through spline or curvic couplinge. These components will suffer
and withstand deflections, temperature gradients, miaalipenta, etc.
Figure 16 ahows a cavitating-type inducer mounted on the shaft with the
pump impeller.
k d e r cond'ition of low inlet Xet Positive Sbction Head
the inducer operates in a cavitating condition but provides a head rise
sufficient to suppress cavitation in the main impeller and thua permit8
it to work satisfactorily. High-speed pumps can, therefore, be operated
at a much lower inlet head than conventional pumps, and the net gain i r
very much lighter and smaller turbomachinery. Figure 17 shows the weight
��Figare 17.
Turbopump weight/turbine nhaft horaepowar vereus
tarbopnmp rotational apeed.
�reduction obtained by increased turbopump rotational speed.
Moet of
Thir
these gains have been made possible by improvements to the inducer.
weight saving is critical in flight hardiiare and is also~importantfor
commercial machinery because lower weight and smaller size often result8
An important parameter for an inducer is the suction
specific speed at which it is able, to operate and develop head. The*
improvement in suction performance obtained by utilizing a low flow coin reduced costs.
efficient inducer is illustrated in Fig. 18.
Conventional pump8 are
limited by head loss from cavitation to a suction apecific speed from
5000 to 8000, whereas rocket engine pumps as a result of inteneive develop-
ment efforts over the years have been improved to 40,000 in water.
r
The important design parameters for an inducer giving approximately
35,000 suction specific speed in water are shown in Table 3.
It is important to note that cavitation performance is poorest in cold
water and other liquids having similar thermodynamic properties.
The
described inducer will give in excess of 40,000 suction specific speed
in liquids (such as liquid oxygen) that are being pumped near their boiling point.
In liquid hydrogen, the auction specific speed attainable
ie over 70,000.
The blades of the inducer at design conditions operate under cavitating
conditions with consequent wear to the inducer and surrounding case.
Thir
is of only minor consideration in short life rocket engine pumps, but i m
a aerious limitation in commercial p m p s that require long-operating life.
It has limited the application of these inducers,but prewhirl offer.
possible means of alleviating this problem.
r
���A great deal of this cavitation can be suppressed and possibly eliminated
if a technique known as prewhirl is used. Figure19 illustrate6 the
application of preb-hirl to the inlet of a cavitating inducer, centrifugal .
pump combination.
Prebhirl consists of bjpaseing a small quantity ot
high-pressure pump discharge flow to the inducer inlet.
This secondary
flow of high-energy fluid swirls around the inlet pipe outside a ~ u l u s
and suppresses inducer backflow and cavitation.
Fig. 20 a and b
.
This is illustrated in
This first photograph indicates the inducer cavitat-
ing during normal pump operation, The second photo shows the same inducer
with prewhirl in operation.
Notice the great reduction in backflow and
mvitation and the general smoothing of the flow.
There is also a large
.
reduction in pump discharge pressure oscillationsbas illustrated in Fig.21
Prewhirl will also increase the suction specific speed of an inducer.
The prewhirl is in the direction of rotation and can thus reduce the
N e r head of the pump.
This is an aid in broadening the operating range,
as the stall range can be extended and efficient operation achieved at
low-flow conditions. Depending on requirements, from 2 to 15 percent of
the p m p flow is bjpaseed for prewhirl.
Bypassing lower head fluid from
the inducer discharge rather than from the pump diecharge offere a means
of reducing the loss associated with the process because of the improved
ejectory efficiency of lover momentum bypass fluid,
.
���Figure 21.
Iduaer osoillation reduotion.
�SEALS
A great deal of development work has been done on rocket engine turbopump
shaft seals. While particular emphasis has been on cryogenics, the reaults
are applicable to seale in other extreme environments. The basic seal
tj-pes are shorn in Fig.22
.
In the past, comercia1 machinery hae ex-
tensively used the packing box seal.
This seal alwaya ha8 Borne leakage
and historically haa been a very troublesome device.
The requirement.
of reduced lehkage, higher shaft speeds, and improved reliability have
resulted in the development of the mechanical aeal.
Normally, an elaetomer
such,as a rubber O-ring has been used on the secondary seal that seals
along the path of the axial movement of the nosepiece carrier.
Severe
operating regimes of both very low and high temperatures have led to the
development of k liptype secondary seal for rocket engine applications.
Dynamic shaft seal developments during the past 2 or 3 years have pointed
out the advantages of using metal bellows-type face seals (Fig.23 ) for
the severe applications of the aerospace industry.
The extreme temperatare
requirements, often from as low as -423 F to as high as +lo00 F, have
directed most of the face-type seal test effort toward the bellows.
The
all-metal construction allowa the seal to operate at temperature6 which
are only 1imited.b~the capability of the metal inatead of this usual
elastomer secondary seal that is used in moat standard applications.
A properly deeigned bellows seal ie capable of withstanding ertremely
high fluid pressure throughout large temperature ranges for long periods
of time without the worry of elaatomer deterioration and cure date expiration.
For this reaeon, the bellows-type seal hae many potential applica-
tione for industrial usage.
At the present time,
t h e bellows eeal is more
��Figure 23.
Bellm Seal.
�expensive than the conventional elastoner t y p e ; however, as the rate of
usage increases and the bellows are fabricated in volume, it is reasonable
to expect that the costa may be comparable. Actually, &en
replacement
costs are considered, the bellows seal may be leas expensive in the long
run, even at present prices.
Mechanical seals operating in a lubricating media auch as oil can have
practically no leakage.
Such is not the case, however, when sealing a
nonlubricant like gaseoue nitrogen.
In this caae, the leakage rates can
have an acceptably low value of 6 scim of gas sealing against 30 pounds
pressure, at 8000 fpm seal surface speed for a 2-inch-diameter seal.
HIGH-LOAD
, HIGH-SPEED
BEARINGS
Ekperimental investigations conducted for space development programs have
been effective in breaking down barriers and extending previously accepted
limitations of speed, loading, and cooling of the rolling contact bearings.
Prior to 1955, 1,000,000 DN (bore in millimeters multiplied by speed in
rpm) was considered to be extremely fast for ball and roller bearings.
Because of the advances in bearing geometry and lubrication techniques
required for turbomachinery applications, bearings operating at 1,500,000
DN are fairly commonplace, and have proved to be reliable. It
was
found,
for instance, that highly loaded roller bearings equipped with inner-land
riding cages are quite difficult to lubricate properly at altitudes of
100,000 feet and more; similar bearings equipped with outer-land riding
cages, providing easy lubricant entry, experienced no difficulty d e r
vacuum environmentr.
\
�It has been found that the maximum compressive stresa existing between
races and rolling elements can be extended almost to the plastic flav
range if proper lubrication techniques are employed.
It ie paramount
to maintain a heat balance in which heat is removed from the bearing at
the rate it is generated at a temperature low enough to maintain proper
materiala properties.
Bearings may be made to accept high loads and speeds with proper lubrication by conventional lubricants such as oils.
However, an advantage c a n
be obtained by using process fluid as the tearing coolant/lubricant.
Fkperimental investigations have shown that with proper material selection,
such fluids as RP-1, LH2, N 0 LRFNA, and X2 can cool high-speed
2 4'
(1,000,000 DN) ball bearings.
In another investigation, it was s h w n that by careful attention to detail
design of ball bearings, the operating speeds and loads can be elrtended
A ball bearing cooled by
3 has been operated for short periods at speeds to 4,000,000 DN, and
for useful duration8 at 3,000,000 DN.
using coolants with little or no lubricity.
.
In summary, it might be stated that experimental programs aimed at
development of rocket engine turbomachinery have freed users of rolling
contact bearings from some of the limitations in apeed, load, and lubricants formerly accepted by induatry in general.
�RECEUT ADVAhCES IN MECMICAL
GEARING TRANSMISSIONS
Between 1958 and 1964 there has been a slow but steady advancement in the
load carrying capacity on aerospace and rocket engine gearing.
There have
been no major breakthroughs but the combination of empirical metallurgy
and better quality control has resulted in gearing with 1-1/2 to 2 times
its previous load carrying ability.
Quality assurance begins with the'rigid control of the alloy composition
and is almost continuous during the pouring, forging, cutting, and heattreating operations.
*
Most of the material for aerospace gears is produked by the double vacuum
melted proceqs using consumable electrodes.
Ektreme cleanliness is a
must and carbon content of the alloy is controlled in some instances
within 0.02 percent.
Heat-treatment cycles are specified and then rigiqly controlled.
are stress relieved in dual cycles of +3OO to -100 F.
Parts
The latest carburiz-
ing furnaces are of the stainless-steel retort type with infrared analysis
and control of the carburizing atmosphere.
Sample slugs and sample parts are subjected to the identical heat-treating
process as the production parts.
The samples must'be acceptable by
metallurgical evaluation before the parts are purchaeed.
Sample parts
are then run at conditions equal or greater than actual operating conditiona.
Failure of a mandacturerls parts to pass these quafificetion
tests means disqualification of the manufacturer aa a supplier.
.
�Improvements in the accuracy of measilriug devices have made it possible
to tighten tolerances and still maintain the ability to measure with
repeatability.
Ten years ago, some manufacturers talked in terms of 0.0001 of an inch
and were able to measure to 0.0002 to 0.0005 inch.
Today, the same people
talk in terms of millionths of an inch and measure repeatedly in a range
of 0.0001 to 0.00005 inch and as low as
5 microinchea.
To accomplish this, the measuring instruments and parts are kept in socalled white rooms where temperature, humidity, and dirt levels are
rigidly controlled.
Surface finishes are now measured as to finish, lay, and waviness.
*
It
has been found that these factors have a ,reat influence on scoring resietence of the gear surface.
Shot peening of gears used in the past, as a corrective measure, is now
part of the original design to induce beneficial compressive stresses and
relieve discontinuities in gear roots, webs, and rims.
Increases of up
to 50 percent improvements in fatigue life have been obtained in some
instances.
The same peening procedures are used on splines and couplings
with similar results.
Improvements have been made in design theory.
Profile modifications used
,
to be a matter of experience.
Today, detailed profile measurements, deflectione, and calculations are
made all along the line of action.
&tire
profile modification8,art
calculated before a gear is run, thus decreasing scoring, finding, and
compressive failure#.
�Root stresses are now calculated with much greater accuracy and loads of
1-112 to 2 times those of a few years ago are being used.
Unit loads of
40,000 t9 45,000 and bending stresses of 80,000 psi are common practice
An index of the compressive strength
of a gear is the K factor. ?reduction gears are running today with K
for life cycles up to 10,000,000.
values of over 2000, whereas
high.
I(
values of 900 used to be conaidered as
Metallurgy and a dimensional accuracy have been the moet important
contributing factor..
Ten years ago, a pitch-line relocity of 20,000 ft/min was considered a
maximum to prevent scoring failures. Today, the ability to more accurately
control gear-face surface conditions and the use of lubricant additives
hare relieved the scoring problem to the extent that pitch line velocities
of 50,000 ft,/min are obtainable.
The greatest area of improvement occurred in lubrication of aerospace
gearing. For example, kerosene by itself can carry only 500 lb/in. of
face loading.
By the addition of 3 percent by volume of extreme pressure
additives, load carrying capacity of over 6000 lb/in. of face has been
demonstrated.
Gears pretested with an extreme pressure film of millionths of an inch
thickness can later be operated in kerosene only at loads up to 4000 lb/in.
It appears it may be feasible to pretreat gears and bearings with extreme
pressure films before putting them in actual service and then nm them
in any reasonable coolant.
#
This theory has been demonstrated under controlled laboratory conditions;
howdver, additional research must be done before it can be applied to
comerical transmissions.
The use of dry-film lubricants is more prevalent
and offers a potential future especially for rpliner.
�Special nitrited surface gears have been run at extremely high temperatures
(600 F) and bearings and couplings have been operated at -300 and -420 F
in gases and liquids of pure oxygen and hydrogen.
LoaQs have aot.been
extremely high on 'gears,but they can carry significant loads (500 to 1000
1b;in.)
for short timee.
Present gears can carry approximately 40 horeepover for every pound of
gear box and with a reliability of as high aa 0.9996.It is felt that the procedures, controls, and experience described could
be applied to everyday industrial applications, resulting in lighter,
more efficient, more reliable industrial products.
a
DEVELOEENT OF ALUMINUM ALLOY
CASTINGS
In the early fifties, design values for ultimate strength and yield strengkh
of castable aluminum alloys were approximately 23,000 and 15,000 psi,
respectively. As a result of considerable research and development work
in the aerospace industries in recent years, one can now confidently use
values of over 45,000 psi ultimate and 56,000 yield.
One of the most widely used general purpose castable aluminum alloys has
been 356-T6.
of the
Imparities like iron, however, limit the heat treatability
356 alloy. The iron forms needle-shaped crystala that are brittle
and it is, therefore, not possible to heat treat the alloy f d l y without
serious damage to ductility.
�The alloy Tens-50 developed at Rocketdyne overcame this defect in 356 by
modifying the shape of the brittle iron crystals to harmless modules
through a beryllium addition. A further improvement was also made by
increasing the heat treatable hardening constituents (magnesium and silicon)
resulting in a higher heat treatable etrength. The composition of 356
and Tens-50 is compared in Table 4.
Succeseful reeults in minimizing casting porosity because of gas or shrinkage have been achieved by the combined effect of controlled melting techniques and extensive me af chills in the mold design.
Normal melting precautions such as control of purity of furnace charges,
proper degassing procedures, and controlled holding and pouring t e m p
,eratures are important in the production of porosity-free aluminum
caatinga.
3
Statistical analysis shows, however, that these precautions do not guarantee consistantly sound castings. When good melting add pouring techniques are combined,with the extensive use of Leary chills in the mold
design, a real improvement is achieved because of the extremely rapid
solidification.
AB an example of the properties achieved in an actual caeting, a Tens 50T60 aluminum alloy sand casting of a turbopump volute was metallurgically
analyzed. This test is part of the routine metallurgical evaluations
that are performed on all Rocketdpe castings. Fifty-two r o d (0,250
inch diameter) teat bars were machined from the casting. Table 5 shows
the results. Ultimate strength as high as 49,800 psi, yield etrength am
high as 38,100 psi and elongations of a maximum of 8.5 percent were obtained.
�TABLE 4
-
b
EIE?Ell"rS
i
Tens-50
356
w
5
si
6.5
%
0.25
- 7.5
7.6 -8.6
0.15 -
- @.LO
0.ho
Be
C
0.10
0.55
0.30
- 0.20
Ti
0.20 Fax
~a
0.13
Cn
0.10 Fax
0.10 Max
m
0.50 F2x
0.20 Fax
Zn
0.05 :?ax
0.20 Max
Al
Reminder
Renainder
- 0.30
0.30 Max
n
�,
f.2
----.
-- .
z'€
-- 6.5.
0
0
1
'
H
CoQ'w2
-
OW' lb
006
'st,
002 'Lt7
006'sC
S'P
S'S
9
C
.
2
o w ' 9~
tr
000 '9c
----
008'SC
0.c
cozg9€
4 'L
-
C.9
-
001'PC
--00%'
Sf
-
ooB'6t7
-..
00 b'btr
009 '
6
000'5~
--
.
I.
--
-
-.-
PJ!fl
I ~ y J- uj O n
l
I!J3
~=ra
.capu!iAa ( ~ I Y I
sI~llnO
Iw!4!J3'U0N
'kern a(n10~
p~epuets
I*!+!'3
c
2 '31t11"5
-
.
I ~ a ( t ! l d -s ~ b 3 p6 ~ 1 1 ~ ~ 1 1
SJb(t!ldS )o J b ( u 8 3
z J@!l!ldS
.
bu!peal
I ~ J ! ) ! J ~ I ~a((!lds'-a6pa
€
c
c.
a)+
~ F ~ ~ I -.on
A J
lm! I!J3'"91
--
I*? l!'3
2
PJWU~S
9
€. 9
s'8
0:L
.---
9
t,
----.
-- --__. .---.
L'c
-.-.
QVO'l3
i
\Pa!\!'J
I=!f!Ja
---
.
15d-0131~
--.
.
zanhol
anhuq-
--
-
a)p3 bu!pes)
NOILV307
3 0 ~ ~ 3
- - -
-
..
�Individual test bare machined from the most significant arear of the
caeting were analyzed microscopically and the resulta are shown in
Fig.24
.
�PHOTOMICROGRAPHIC STUDY AND MECHANICA PROPERTIES OF F-1 FUEL VOLUTE
TENS 50-160 ALUMINUM ALLOY SAND CASTING. WEIGHT OF CASTING: 400 POUNDS
3.0% ELONG
39.300 PSI
2.0%ELONO
49.200 PSI
43,700 tL(
36.206 PSI
4.0% ELOW
6.0%ELOW
Figure 24.
Photomicrographic etudy and mechanical propertier
o f P-1 Fnel Volute Tern 5 0 - ~ 6 0Alnminnm Alloy Sand
cmting. Weight of casting: 400 pound..
55
�
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Title
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Saturn V Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
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Saturn V Collection
Description
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<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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spc_stnv_000036
Title
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"Advances in Pumping Technology and Rocket Engine Turbopump Applications."
Description
An account of the resource
Presented by Charles A. MacGregor, Supervisor, Advanced Turbomachinery during Workshop D, Royce Hall, Room 160 at UCLA on 2 June 1964, as a part of the NASA-UCLA Symposium and Workshop on the Transformation of Knowledge and Its Utilization. The introduction notes, "This report is divided into two general parts. The first part is a description of turbopumps for liquid rocket engines as they exist today. For completeness and understanding, some background information is included on why turbopumps have evolved to their present configurations. The second part suggest portions of this effort that may have some applicability to the general economy."
Creator
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MacGregor, Charles A.
North American Aviation. Rocketdyne Division
Date
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1964-06-02
Temporal Coverage
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1960-1969
Subject
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Saturn Project (U.S.)
Liquid propellant rockets
Turbine pumps
Turbomachinery
Type
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Reports
Text
Source
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Saturn V Collection
Box 11, Folder 33
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
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en
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This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
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spc_stnv_000027_000050
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/10424/scan0006rev_080107120531.jpg
001b544c8321dde620442ec2c7809aa3
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Title
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Saturn V Collection
Relation
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<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
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Saturn V Collection
Description
An account of the resource
<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
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scan0006rev_080107120531.jpg
spc_stnv_000780
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S-IVB cutaway and J-2 engine."
Description
An account of the resource
8 x 10 inch black and white diagram of the JII engine and the Saturn IV.
Creator
An entity primarily responsible for making the resource
George C. Marshall Space Flight Center. Propulsion & Vehicle Engineering Laboratory.Metallurgical Analysis Section. Materials Division, Metallic Materials Branch
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Saturn project
Apollo project
Saturn launch vehicles
Liquid propellant rockets
Apollo project
Saturn S-4B stage
Liquid propellant rocket engines
J-2 engine
Type
The nature or genre of the resource
Still Image
Diagrams
Source
A related resource from which the described resource is derived
Saturn V Collection
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Is Part Of
A related resource in which the described resource is physically or logically included.
Is referenced by: Materials in space exploration.; Is part of: Envelope - Photos Accompanied C. E. Cataldo paper "Materials in space exploration".
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
spc_stnv_000775_000799
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/10555/satuIfirsgene_062007153848.pdf
a8dffe5d84348cfe518c8ab286f97766
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Saturn V Collection
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Saturn V Collection
Description
An account of the resource
<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
satuIfirsgene_062007153848.pdf
spc_stnv_000717
Title
A name given to the resource
"Saturn I : the first generation of heavy launch vehicles designed for peaceful exploration of space."
Description
An account of the resource
A basic description of the Saturn rockets alongside diagrams for context.
Creator
An entity primarily responsible for making the resource
George C. Marshall Space Flight Center. Public Affairs Office
Date
A point or period of time associated with an event in the lifecycle of the resource
1964-01-01
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Saturn project
Saturn 1 launch vehicles
Saturn launch vehicles
Liquid propellant rockets
Liquid propellant rocket engines
Type
The nature or genre of the resource
Text
Reports
Source
A related resource from which the described resource is derived
Saturn V Collection
Box 10, Folder 20
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
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spc_stnv_000700_000724
Is Referenced By
A related resource that references, cites, or otherwise points to the described resource.
http://libarchstor.uah.edu:8081/repositories/2/archival_objects/16892
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/10581/satsivcryoweighsyst-I_072007112534.pdf
317797ff45896bad6defe9a0bf137422
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Saturn V Collection
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Saturn V Collection
Description
An account of the resource
<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
satsivcryoweighsyst-I_072007112534.pdf
spc_stnv_000693
Title
A name given to the resource
"Saturn S-IV cryogenic weigh system. Part I : propellant utilization."
Description
An account of the resource
In order to achieve maximum vehicle efficiency, it is essential that the vehicle propellants be loaded to desired values and that these propellants approach simultaneous depletion at the end of powered flight. To accomplish precise loading and assure minimum residuals, a highly accurate and repeatable, vehicle located, propellant management (PM) or propellant utilization (PU) system must be used. As the ability to load propellants to predetermined values depends directly on the ability of the system to accurately sense the propellant masses, it is essential that the system be calibrated with respect to propellant mass under conditions resembling those to be experienced during final loading and powered flight. The use of a cryogenic weight system will reduce the unknown factors in capacitance sensor element shaping, tank geometry, and propellant properties to a degree which will permit the determination of propellant masses to with .025%.
Creator
An entity primarily responsible for making the resource
Nichols, R. H.
Date
A point or period of time associated with an event in the lifecycle of the resource
1965-06-20
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Liquid propellant rockets
Cryogenic rocket propellants
Saturn S-4 stage
Type
The nature or genre of the resource
Text
Reports
Source
A related resource from which the described resource is derived
Saturn V Collection
Box 14, Folder 15
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
spc_stnv_000675_000699
Is Referenced By
A related resource that references, cites, or otherwise points to the described resource.
http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17162
-
http://libarchstor2.uah.edu/digitalcollections/files/original/20/10580/satsivcryoweighsyst_072007101249.pdf
17cfd3ced4f9086134a3da162c1067aa
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Title
A name given to the resource
Saturn V Collection
Relation
A related resource
<a href="http://libarchstor.uah.edu:8081/repositories/2/resources/60" target="_blank" rel="noreferrer noopener">View the Saturn V Collection finding aid in ArchivesSpace</a>
Identifier
An unambiguous reference to the resource within a given context
Saturn V Collection
Description
An account of the resource
<p>The Saturn V was a three-stage launch vehicle and the rocket that put man on the moon. (Detailed information about the Saturn V's three stages may be found<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_first_stage.html">here,<span> </span></a><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_second_stage.html">here,<span> </span></a>and<span> </span><a href="https://www.nasa.gov/centers/johnson/rocketpark/saturn_v_third_stage.html">here.</a>) Wernher von Braun led the Saturn V team, serving as chief architect for the rocket.</p>
<p>Perhaps the Saturn V’s greatest claim to fame is the Apollo Program, specifically Apollo 11. Several manned and unmanned missions that tested the rocket preceded the Apollo 11 launch. Apollo 11 was the United States’ ultimate victory in the space race with the Soviet Union; the spacecraft successfully landed on the moon, and its crew members were the first men in history to set foot on Earth’s rocky satellite.</p>
<p>A Saturn V rocket also put Skylab into orbit in 1973. A total of 15 Saturn Vs were built, but only 13 of those were used.</p>
Dublin Core
The Dublin Core metadata element set is common to all Omeka records, including items, files, and collections. For more information see, http://dublincore.org/documents/dces/.
Identifier
An unambiguous reference to the resource within a given context
satsivcryoweighsyst_072007101249.pdf
spc_stnv_000692
Title
A name given to the resource
"Saturn S-IV cryogenic weigh system. Part IV : safety."
Description
An account of the resource
During cryogenic weigh system operation, hydrogen when combined with oxygen can create an unsafe condition. Therefore the concentration of the residual oxygen and hydrogen from leaks in the cryogenic weigh environmental bags must be known at all times during the cryogenic weigh. Hydrogen and oxygen detectors will provide the optimum method for maintaining safe conditions. Hydrogen properties and safe mixtures are reviewed. The method selected to analyze the oxygen content is discussed. The selection, development, and testing of a hydrogen detector system is examined.
Creator
An entity primarily responsible for making the resource
Corcoran, Edward G.
Date
A point or period of time associated with an event in the lifecycle of the resource
1965-06-20
Temporal Coverage
Temporal characteristics of the resource.
1960-1969
Subject
The topic of the resource
Liquid propellant rockets
Cryogenic rocket propellants
Safety
Type
The nature or genre of the resource
Text
Reports
Source
A related resource from which the described resource is derived
Saturn V Collection
Box 14, Folder 8
University of Alabama in Huntsville Archives, Special Collections, and Digital Initiatives, Huntsville, Alabama
Language
A language of the resource
en
Rights
Information about rights held in and over the resource
This material may be protected under U. S. Copyright Law (Title 17, U.S. Code) which governs the making of photocopies or reproductions of copyrighted materials. You may use the digitized material for private study, scholarship, or research. Though the University of Alabama in Huntsville Archives and Special Collections has physical ownership of the material in its collections, in some cases we may not own the copyright to the material. It is the patron's obligation to determine and satisfy copyright restrictions when publishing or otherwise distributing materials found in our collections.
Relation
A related resource
spc_stnv_000675_000699
Is Referenced By
A related resource that references, cites, or otherwise points to the described resource.
http://libarchstor.uah.edu:8081/repositories/2/archival_objects/17165