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US 6,834,493 B2 34 propellantA isloWatthetimeofthisin?ow,thereisonly slight pressure loss inside the heat exchanger 2, and the temperature decrease resulting from heat exchange is more than bene?cial enough to compensate for the decrease in pressure due to this pressure loss. As a result, as Will be described below, cavitation is reduced Within the pump 1. The propellants A and B are then supplied to the rocket engine combustion chamber 5. NPSH=(pump inletpressure-saturatedvaporpressure)/?uidden sityatpump inlet/gravitationalacceleration This value represents the margin up to the evaporation pointofa?uid,andthelargeristhisvalue,thegreateristhe margin before cavitation occurs. FIG. 5 is a graph of the NPSH When the liquid oxygen temperature is decreased as shoWn in FIG. 3. The verticalaxisistheNPSH oftheliquidoxygen after heat exchange, and the horiZontal axis is the liquid hydrogen ?ux/liquid oxygen ?ux. As shoWn by this graph, FIG. 2 is a concept diagram illustrating the constitution of anotherembodimentinWhichthepumpsystempertainingto10 Whennoheatexchangerisusedasinthepast,thisNPSHis the present invention is applied to the propellant supply system of a liquid rocket engine. Only the differences from the above embodiment Will be described. 27 m. In contrast, With the embodiment of the present invention, under conditions in Which the propellant ?ux ratio (hydrogen?ux/oxygen?ux)is0.16,theNPSH is32.2m, Whichmeansthatanimprovementofabout20% inthe Inthisembodiment,numeralAisapropellant,numeralC is a coolant that serves as a loW-temperature source for 15 suctionperformancecanbeanticipated. coolingtheenginenoZZle,andnumeralD isapropellant other than the propellant A. With this system, a ?uid With a loWer temperature than the propellant A is used as the coolant C, and this is utiliZed as the loW-temperature source tocoolthepropellantA.Forexample,Whenthepropellant20 mately300kPainastateinWhichtheliquidoxygen A isliquidoxygen,thecoolantC isliquidhydrogen,Which has a loWer temperature than liquid oxygen. When the propellant A is liquid hydrogen, the coolant C is slush hydrogen, for example, Which has a loWer temperature than liquidhydrogen. In the above embodiment, the described structure pre vented the occurrence of cavitation in the pump for the propellant A, but it should go Without saying that With a rocketengineofthetypethatburnsapluralityofpropellants as in this embodiment, cavitation can also be reduced in the pump (notshoWn)fortheotherpropellantD byloWeringthe temperatureofthepropellantD WiththecoolantC,justWith the propellant A. For instance, When the propellant D is lique?edmethane,thetemperatureofthepropellantD can be loWered by using liquid hydrogen as the coolant C. FIG. 3 is a graph of liquid oxygen temperature versus hydrogen/oxygen ?ux ratio When liquid hydrogen isused to loWertheliquidoxygentemperaturethroughheatexchange in the embodiment shoWn in FIG. 1. aftTerhehevaetrteixccalhaanxgies,iWshithle ltihqeuihdoroixZyongteanl taeximspeirsatuhreeratio betWeen the liquid hydrogen ?ux and the liquid oxygen ?ux. Here, the liquid oxygen prior to heat exchange has a temperature of 90K and a pressure of 400 kPa, While the liquid hydrogen prior to heat exchange has a temperature of 50K and a pressure of 10 MPa. The temperatures of the tWo ?uids are equal after heat exchange. As a result, in a typical case in Which the propellant ?ux ratio (liquid hydrogen ?ux/liquid oxygen ?ux) in a liquid hydrogen-liquid oxygen rocket is 0.16, it can be seen that the liquid oxygen tem perature after heat exchange decreases to about 65K. FIG. 4 is a graph of the saturated vapor pressure of liquid oxygen When the temperature decrease shoWn in FIG. 3 is obtained. The vertical axis is the saturated vapor pressure (kPa) of the liquid oxygen after heat exchange, While the horiZontal axis is the ratio betWeen the liquid hydrogen ?ux and the liquid oxygen ?ux. As shoWn in the draWing, the saturated vaporpressureoftheliquidoxygenisgreatlyloWeredby 60 heat exchange, making it much less likely that cavitation Will occur. Ingeneral,thevalueobtainedbysubtractingthesaturated vapor pressure from the inlet pressure and expressing this pressure as the height of a Water column is termed the Net 65 Positive Suction Head (NPSH), expressed by the folloWing equation. MeanWhile,iftheNPSH isthesame27m asWhennoheat exchange is performed, the required pump inlet pressure under conditions in Which the propellant ?ux ratio (hydrogen ?ux/oxygen ?ux) is 0.16 decreases to approxi temperature has been loWered to 65K by heat exchange. Speci?cally, itcan be seen that the pump system pertain ing to the present invention loWers the pressure inside the propellant tank by loWering the pump inlet temperature. As 25 aresult,theWallsofthepropellantcanbemadethinner, Which makes the tank more lightWeight. Also, as can be seen from the above equation expressing theNPSH, thesmalleristheNPSH ofapump inastatein Which no heat exchange is performed, that is, the smaller is thedifferencebetWeentheinitialpump inletpressureandthe saturated vapor pressure, the greater Will be the effect of loWering the saturated vapor pressure at the pump inlet. As discussed above, the occurrence of cavitation is reduced With the present invention, Which alloWs the pro 35 pellanttankpressuretobedecreased,andthismeansthatthe propellant tank can have thinner Walls and be more lightWeight, and this increases the Weight that the rocket engineiscapableoflaunching. Also, reducing the occurrence of cavitation makes it 40 possibletoraisethepumpspeed,andleadstoreductionsin pump siZe and Weight. Furthermore,raisingthepump speedincreasestheattain able pump pressure, alloWs the rocket engine operating pressure to be higher, and alloWs the overall siZe and Weight 45 oftheenginetobereduced. Also, raising the rocket engine operating pressure increases the pressure level inside the noZZle doWnstream from the combustion chamber, alloWing the combustion gas toexpandtoalargeroutletsurfacearea,boostingthespeci?c 50 thrust,andevenleadingtoareductioninfuelconsumption. What is claimed is: 1.A systemreducingpump cavitationinarocketpump systemcomprising: a reservoir tank as a ?rst ?uid source operative to store a ?rst ?uid, said ?rst ?uid being a liquid; a heat exchanger; a rotary pump as a ?rst pump; a ?rst ?uid path operative to enable passage of only said ?rst ?uid from said ?rst ?uid source through said heat exchanger to said ?rst pump; a second ?uid source operative to supply a second ?uid Which has a loWer temperature than said ?rst ?uid; a second pump, and a second ?uid path operative to enable passage of said second ?uid from said second ?uid source through said second pump to said heat exchanger;PDF Image | SYSTEM FOR REDUCING PUMP CAVITATION
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