Storag of helium gas at higher temperature and pressure using liquid hydrogen refrigerant to surround primary fluid within inner vesse

Bald, W. B.

English

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https://ntrs.nasa.gov/search.jsp?R=19690010053 2020-03-12T07:40:45+00:00Z
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DEVELOPMENT OF AN
SPS/DPS HYDROGEN SHROUDED
CRYOGENIC HELIUM STORAGE
SYSTEM
Fl
CONTRACT: NAS9 +7337
SUMMARY REPORT
PREPARED FOR:
-N L AERONAUTICS NNATIO A	 AN D
SPACE ADMINISTRATION —
MANNED SPACECRAFT CENTER
HOUSTON, TEXAS 77058
PRESENTED BY:
THE BENDIX CORPORATION	 ,.r
'NSTRUMENTS E LIFE
SUPPORT DIVISION
DAVENPORT, IOWA 52808
PREPARED BY:
t	 Wo B. BALD
PUB NO, ,  04o-68
v	
S G O ,
	 33-12939
J 8 OCTOBER 1968 	¢^
Lif S Instruments
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ntly being used as the
Lunar Module. The
Into the dewar in a
ground stand-by equip-
sensitive to atmospheric
the amount of usable
Cryogenically stored supercritical helium gas is prese
pressurant for on-board propellant tanks on the Apollo
present system requires that the helium be transferred
sub-critical 'liquid state which involves sophisticated
meet to Fill the unit This transfer' approach is also
conditions which can effect the final helium state and
pressurant stored,,
An alternative approach to the above method is to store the helium gas at a
higher temperature and pressure using a secondary cryogenic fluid, This
concept can be achieved by adopting the Bendix developed integral shroud system
whereby the secondary fluid is Lised as a refrigerant surrounding the primary
fluid contained within the inner vessel.
By using the shroud tankage method, all the environmental heat leak is inter-
cepted by the secondary fluid which vents to atmosphere leaving the primary
helium unaffected by this standby period.
The objective of the NAS9-7337 contract was to develop and test a cryogenic,'
hydrogen shrouded helium storage and supply system, The system was sized for
the Lunar descent and service module propulsion systems requirements.
The system described herein and shown in Figure 5 was successfully tested to
approximate LM requirements and demonstrated the improved ground servicing
and flight standby characteristics over the current SPS/DPS system,
This program was a -follow on to contract NAS9 R 4634, Because of the sisriifi
cant improvement of the shroud concept and application potential to Propulsion
Systems, it is recommended that this program be extended to 'include qualifi-'
cation for Lunair Module application.
IIA STUDY OBJECTIVES
The ove ra'I l objective of this
'
development  c;ontract was to upgrade the In teg ral
shroud tank concept initially developed under a'previous NAS9-4634 contract to
meet the approximate LM descent propulsion systdm requirements. In this respect,
the'increased size of components compatible with the helium pressurant storage
requirements was a major factor.
Study objectives'also included the development of a dewar,container with maxi-
mum reproducible and reliable heat` leak characteristics to meet p'r'olonged pre-
launch and on-board standby requirements,
1 I I r RELATIONSHIP TO OTHER NASA EFFORTS
The effectiveness of the shrouded dewar concept for both pre-launch and in-flight
standby storage of various `c ryogens was c tear 1 y demonstrated by the results of
NASA contract'number NAS9-'4634 carried out by The Bendix Corporation, Instruments
& Life ' Support Division for the Propulsion & Power Division of NASA-MSC,' Refer-
ring 'in-particular to the primary storage of helium enshrouded by various sub
critical refrigerants; Figures 1, 2, 3 and 4 reproduced from this report illu-
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strate the advantages of using hydrogen as the secondary fluid, Theses curves
showed that a hydrogen shrouded helium system operating at about 2000 psia
provides the best weight optimized storage system for both pre-launch and on-
board standby The curves also showed that a dewar design which Incorporates
two d iscrete radiation shields with the inner shield being vapor cooled by the
evaporated shroud Fluid provides optimum design capabilities,
IV. METHOD OF APPROACH & PRINCIPLE ASSUMPTIONS
The helium tankage assembly designed and constructed under the present contract
employs the recommendations contained in the NAS9-4634 final report.
The basic design of Figure 6 Is a dual wall vacuum dewar employing the Bendi x
developed discrete radiation shielded concept using two shields with the inner
shield being vapor cooled by tho vented hydrogen,
E	 The dewar is designed to store 50,0 pounds of helium at 2000 psia and 37'R by
enshrouding the helium gas with liquid hydrogen at standard atmospheric conditl-
tions.
B y employ ing the integral shroud design concept, the vacuum void exists between
the srodan  enclosing outer shell thus reducing the environmental heat leak
to a mainly radiative heat transfer mode,
The Bendix developed radial bumper suspension system is used to suspend the Inner
vessel and shroud assembly concentric within the enclosing spherical outer shelf
t	 d con tai ned	 t	 e hWrapped around the inner vessel ou er surface wi h in th  shrou d
annulus is 1/8" thick Teflon felt which is aimed at providing a "wicking action"
for the liquid hydrogen in the shroud and thus improve system standby capablli-
ties,
Because of tooling availability and the possibility of overall size reduction,
a tapered shroud annulus which tapers from the poles to the equator Is used in
the designs This also provides a comparison between the concentric annulus
shroud geometry used on the NAS9-4634 unit and a tapered geometry.
'The basic dewar assembly Is mounted in a cradle-type mount carriage which provides
six point center plane attachment'between the tankage assembly and the vehicle
or propellant cascade system,
External components and valves used to operate the system of Figure 7 are
conveniently attached to the mount carriage arms and a remotely operated control
panel is supplied which can control the operation of the valves or monitor
temperatures and pressures from a distant location,
V^ BASIC DATA GENERATED AND SIGNIFICANT RESULTS
Section III of the main report discusses In detail the theoretical analysis
performed within the scope of the contract. This work includes a structural
analysis of the mount carriage which supports the dewar, an Investigation
into the dynamical characteristics of the radial bumper suspension system
and an outline of the heat transfer equations used to predict the thermal
performance of the unit.
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1. INNER PRESSURE VESSEL
2. TEMPERATURE SENSOR SUPPORT TUBE
3, TEMPERATURE SENSOR LEADS
4. TEFLON FELT
5. SHROUD
6, INNER VAPOR COOLED RADIATION SHIELD
7, OUTER RADIATION SHIELD
8. OUTER SHELL
9, SHROUD VENT FITTING
10,INNER VENT TUBE
11,ION PUMP
12,ELECTRICAL LEAD FITTING
13,FLUID OUTLET VENT FITTINGS
14,SHIELD HANGER ASSEMBLY
15,SHIELD TO SHIELD SPACER
rF, VAPOR COOK TUBING
17, RUPTURE{ DISC
18. INNER FILL a SUPPLY TUBE
19, SHROUD FILL FITTING
20. RADIAL BUMPERS
21. VAPOR COOL OUTLET FITTING
22, FLUID INLET FILL FITTINGS
FIGURE 6
HELIUM SHROUD TANK DEWAR ASSEMBLY
8
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An extensive testing program was carried out on the completed unit to verify
its structural and thermal capabilities,
A series of LN2 and LH 2 vented heat leak tests were car ried out which resulted
in the equ ilib rium neat leak values listed in the attached Table 1, These
values are compared with the NAS9- 463 1+ unit on a heat leak/unit  area of shroud
surface basis,, 	 it can be concluded from these results that the heat leak
performance of the NAS9 -7337 unit compares favorably with the performance
of the or,ginal shrouded dewar.
The plots of all the vented heat leak tests illustrate the reduction in shroud
heat interception as the liquid level in the shroud decreased. This occurs
in conjunction with a rise in the heat leak into the inner vessel. Figure
8 shows typical experimental results obtained from the vented heat leak tests,
Vapor cooled and non-vapor , cooled GHe pressure buildup tests were performed
on the unit with LH2	 in the shroud.	 These tests	 indicated a maximum standby
capability of	 IN hours	 for the unit without 	 replenishing	 the hydrogen	 in
the shroud.
A significant	 Factor, r`esult'ing from the thermal	 tests on	 the unit was	 the
increase in total	 equilibrium heat	 leak which occurred between the LH 2 vented
heat	 leak data and	 the pressure build-up data.	 This was attributed to 	 increased
bumped contact caused by pressure expansion of the 	 inner vessel	 but	 is a design
aspect which	 requires	 further	 investigation.
A system flow and pressure decay test were performed on the tankage assembly
'itwhen	 .reached maximum operating pressure conditions, 	 This	 resulted	 in a
maximum GHe mass	 flow capability of 0,8 	 lbs/sec.
The completed he'ilum storage system was subjected to modified LM spectrum
random and sinusoidal 	 vibration	 inputs along	 the three principal	 axes of the
unit,	 These	 tests	 resulted	 in full	 compliance with	 the specified	 levels of
random	 'input excitation and showed the need for further study 	 in certain areas
of the sinusoidal	 input spectrum.	 Theoretically predicted	 resonance points
were	 un good agreement with the measured output 	 response of the unit:.for
Vented heat	 leak testserformed on the tankage assembly after vibration testingp	 9	 Y
showed that the thermal	 performance was unaffected by the dynamical 	 loadings.
if Vi,
	 i.iMiTA'T'iONs
Two basic limitations are inherent in the NAS9.7337 design in relation to
the Apo lio LM descent propulsion system requirements.
A design upgrading from a structural standpoint is necessary to meet'the present
LM sinusoidal vibration input levels'. This can be accomplished by suitable
x`	 pre-loading of the bumper suspension system during assembly of the unit.
10
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The tapered shroud geometry, chosen mainly on a basis of existing tooling,
reduced the standby capabilities of the shroud design by a significant degree.
The alternative shroud geometries shown on the attached Figure 9 can considerably
extend the mission duration of a shrouded unit.
VII .	 iMPbiCATIONS FOR RESEARCH
The work performed under this contract and described in the main report confirms
the recommendations put forward In the NAS9 -4634 contract. A hydrogen shrouded
helium storage dewar can be designed and fabricated to store any quanitity
of GH at densities greater than the present lunar module SHe pressurization
system, This increased density allows the storage of the same pressurant
quantity in a smaller tankage envelope.
An indefinite pre-launch standby capability is available with a shroud tank
without loss of primary stored fluid provided the shroud liquid Is replenished
at certain intervals. The unit constructed under the present contract to
approximate LM descent propulsion  system requirements 'wou 1 d require LH2 replen-
ishment approximately every 100 hours of ground standby without loss of GH .
This ground standby capability can be increased by a factor of 3 by adopting
one of the shroud geometries shown In Figure 9.
Preliminary theoretical analysis of the alternative shroud geometries shown
in Figure 9 produced the shroud heat interception curves of Figure 10 and
the corresponding syc,tem,standby curves of Figure 11. The extremely significant
impiicat.ions contained In these theoretical curves suggest the need for further
research effort Into the heat transfer mechanics between the primary and
secondary fluids 'in relation to the shroud annulus geometry.
V1Ii6 SUGGESTED ADDITIONAL EFFORT
The development work carried out on the NAS9-4634 and current programs have
c'learily shown the feasibility of an integral shrouded cryogenic storage
system. Application of this type of unit to future space storage dewars
should be seriously considered for life support and reactant supply systems
in addition to propellant pressurization systems. In this respect, the shrouding
of Ignitible cryogens by inert gases during prelaunch standby is worth consider-
at'ionn
it is recommended that the hydrogen shrouded helium pressurization system
described in this report be upgraded to meet the present lunar module pre-
launch and on-board propellant tankage standby requirements. This upgrading
should adopt an approach similar to the task breakdown shown on page 15 concen-
trating part'icularily on providing a weight optimized unit which satisfi.,es
the anticipated LM vibration . spectrum requirements.
To achieve this upgrading the adoption of one of the two alternative shroud
geometries, shown by Figure 11 to considerably extend standby capabilities,
is recommended,
Adoption of the concentric shroud annulus should be carried out in conjunction
with the use of a cryoformed stainless steel inner vessel which would provide
a 25% reduction of the pressure vessel weight. This annulus geometry would
13
Oendixj Instruments &
Life Support
Division
inc o ease the overai`^ tankage envelope from 29 3/4 inches to 31 inches resulting
in an approxvmate overall tankage weight reduction of 20% and a mission standby
capability of 125 hours.
The glass-fiber reinforced (GFR) oblate spheroidal inner vessel with metal
linen can p,^ovide an inner pressure vessel weight reduction of between 25 and
50% dependdng on the liner material, The possible disadvantages of vacuum
outgassing and plating associated with the composite surrounding this type
of vessel do not appiy to the shrouded dewar concept.
Adopting aluminum to! the GFR pressure vessel liner would allow the use of
this mat.eriai for the shroud which would save a further 30% in shroud weight.
The shroud annu l us geometry associated with a GFR inner vessel would again
► nc;f ease the overall tankage envelope from 29 3/4 inches to 31 inches resulting
in an ove r aii tankage weight reduction of 30% and a mission standby capability
of approximately 340 hours,
Ne above increased tankage envelope sizes compare favorably with the existing
LM supercri t cai he'l'ium pressurant tanks which have an envelope of 33 inches,
It is fw ther ,,ecommended that improved structural and dynamic performance
of the shrouded unit should be pursued by extending the analysis contained
in Section iii of the main report. This would be specifica lly aimed at the
effect of var.ous pc^e -loading techniques on eliminating the non-linear shock
loads experienced by the dewar during vibration.
14
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Development of an SPS/DPS hydrogen shrouded cryogenic helium storage system Summary report

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