Volume 37 Issue 4
Apr.  2022
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SUN Jiguo, CAI Guobiao. Cooling performance of hydrogen for transpiration cooling structure made by different materials[J]. Journal of Aerospace Power, 2022, 37(4): 781-790. doi: 10.13224/j.cnki.jasp.20210187
Citation: SUN Jiguo, CAI Guobiao. Cooling performance of hydrogen for transpiration cooling structure made by different materials[J]. Journal of Aerospace Power, 2022, 37(4): 781-790. doi: 10.13224/j.cnki.jasp.20210187

Cooling performance of hydrogen for transpiration cooling structure made by different materials

doi: 10.13224/j.cnki.jasp.20210187
  • Received Date: 2021-04-22
  • Publish Date: 2022-04-28
  • In order to achieve effective cooling of high temperature and large heat flux combustion devices in aerospace and other fields,the transpiration cooling performance of hydrogen for structure made by different materials and processes under high temperature and high flux density was studied.To simulate the structural characteristics and high heat flow of the high-pressure thrust chamber,a transpiration-cooling test piece was designed,and the mainstream air was heated by an electric arc to generate high-temperature gas.Hydrogen perspiration coolant was applied to 33 thermal tests for 172 seconds on porous ceramics,sintered porous stainless steel and porous laminate materials.The tested material had a porosity of 10%-40%,a combustion chamber pressure of 2.7-8.4 MPa,a mainstream gas temperature of about 3 600 K,a mainstream air flow rate of 220-1 490 g/s,a cooling hydrogen flow rate of 9.6-57 g/s,and an injection rate of 0.005-0.029.Test results showed that when the injection rate of hydrogen perspiration cooling was 1%,the heat exchange between the mainstream high-temperature gas and the walls of both the porous ceramics and the sintered porous stainless steel was reduced by more than 30% and 70%,respectively; when the injection rate of hydrogen perspiration cooling was 3%,the heat exchange between the mainstream high-temperature gas and the walls of the porous laminate materials was reduced by more than 60%.Hydrogen transpiration cooling can effectively reduce the convective heat flow between the wall and the gas.Furthermore,the performance correlation of high pressure,large heat flow and normal temperature hydrogen perspiration cooling was summarized.

     

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  • [1]
    ECJERT E R G,CHO H H.Transition from transpiration to film cooling[J].International Journal of Heat and Mass Transfer,1994,37(Suppl.1):3-8.
    [2]
    WANG J H,MESSNER J,STETTER H.An experimental investigation of transpiration cooling:Part Ⅰ an application investigation on infrared measurement technique[J].International Journal of Rotating Machinery,2003,9(3):154-163.
    [3]
    WANG J H,MESSNER J,STETTER H.An experimental investigation of transpiration cooling:Part Ⅱ comparison of cooling methods and media[J].International Journal of Rotating Machinery,2004,9(10):355-363.
    [4]
    林杨,孙冰,郑力铭.层板推力室发汗冷却壁温特性的初步研究[J].航空动力学报,2008,23(5):877-881.
    [5]
    YANOVSKE L S.Physical basis of transpiration cooling for engines of flying apparatus[M].Moscow,Russia:MAI Press,1996.
    [6]
    HERMANN T,MCGILVRAY M.Analytical solution of flows in porous media for transpiration cooling applications[J].Journal of Fluid Mechanics,2021,915:1-16.
    [7]
    HE Fei,WU Nan,ZHOU Zihe,et al.Experimental investigation on transpiration cooling using propylene glycol aqueous solution[J].International Journal of Thermal Sciences,2021,164:106890.1-106890.10.
    [8]
    CHEN Yu,DU Shen,LI Dong,et al.Numerical investigation of transient phase-change transpiration cooling based on variable properties of coolant[J].Applied Thermal Engineering,2021,184:116204.1-116204.13.
    [9]
    LANDIS J,BOWMAN W.Numerical study of a transpiration cooled rocket nozzle[R].Lake Buena Vista,Florida,US:the 32nd Joint Propulsion Conference and Exhibit,1996.
    [10]
    KEENER D,LENERTZ J,BOWERSOX R,et al.Transpiration cooling effects on nozzle heat transfer and performance[J].Journal of Spacecraft and Rockets,1995,32(6):981-985.
    [11]
    GREUEL D,HERBERTZ A,HAIDN O,et al.Transpiration cooling applied to C/C liners of cryogenic liquid rocket engines[R].Fort Lauderdale,Florida,US:the 40th AIAA/ASME/SAE/ASEE/JPC Conference and Exhibition,2004.
    [12]
    ZHONG Fengqun,BROWN G.Experimental and numerical studies of multi-hole cooled ceramic matrix composite liners[R].Rena,Nevada,US:the 43rd AIAA Aerospace Sciences Meeting and Exhibit,2005.
    [13]
    TANG Jie,CHEN Yufeng,SUN Jiguo,et al.Properties and application of oriented porous SiC as transpiration cooling materials[J].Key Engineering Materials,2007,336/337/338:1109-1112.
    [14]
    TERRY E,CARAS G J,Transpiration and film cooling of liquid rocket nozzles[R].Redstone Scientific Information Center,RSIC-535,1966.
    [15]
    HAESELER D,MADING C,RUBINSKIY V,et al.Experimental investigation of transpiration cooled hydrogen-oxygen subscale chambers[R].Cleveland,US:the 34th AIAA/ ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,1998.
    [16]
    王燚,郭章,王桂香.液氢液氧发动机用丝网多孔发汗冷却面板材料[J].宇航材料工艺,1986(5):40-47.
    [17]
    KAYS M W,CRAWFORD M E.Convective heat and mass transfer[M].3nd ed New York :McGraw-Hill,1993.
    [18]
    MEINERT J,HUHN J.Turbulent boundary layers with foreign gas transpiration[J].Journal of Spacecraft and Rockets,2001,38(2):191-198.
    [19]
    WOODRUFF L W,LORENZ G C.Hypersonic turbulent transpiration cooling including downstream effects[J].AIAA Journal,1966,4(6):969-975.
    [20]
    WHEELER H L,DUWEZ P.Heat transfer through sweat cooled porous tubes[J].Journal of Jet Propulsion,1955,25(10):519-524.
    [21]
    BERGMAN T L,INCROPERA F P,DEWITT D P,et al.Fundamentals of heat and mass transfer[M].New York,US:John Wiley and Sons,2011.
    [22]
    LANGENER T,WOLFERSDORF J V,STEE-LANT J.Experimental investigations on transpiration cooling for scramjet applications using different coolants[J].AIAA Journal,2011,49(7):1409-1419.
    [23]
    DITTUS F W,BOELTER L.Heat transfer in automobile radiators of the tubular type[J].International Communications in Heat and Mass Transfer,1985,12(1):3-22.
    [24]
    LIU Yuanqing,JIANG Peixun,JIN Shaoshan,et al.Transpiration cooling of a nose cone by various foreign gases[J].International Journal of Heat Mass Transfer,2010,53(23/24):5364-5372.
    [25]
    刘元清.发汗冷却基础问题的实验研究和数值模拟[D].北京:清华大学,2010.
    [26]
    熊宴斌.超声速主流条件发汗冷却的流动和传热机理研究[D].北京:清华大学,2013.
    [27]
    LEZUO M,HAIDN O.Transpiration cooling in H2/O2-combustion devices[R].Lake Buena Vista,Florida,US:the 32nd Joint Propulsion Conference and Exhibit,1996.
    [28]
    ZINNER W,HAESELER D,MAEDING C,et al.Development of advanced technologies for future cryogenic thrust chamber applications[R].Washington,US:the 33rd Joint Propulsion Conference and Exhibit,1997.
    [29]
    SERBEST E,HAIDN O,GREUEL D,et al.Effusion cooling of throat region in rocket engines :applying fibre reinforced ceramics[R].Salt Lake City,Utah,US:the 37th Joint Propulsion Conference and Exhibit,2001.
    [30]
    FROEHLKE K,HAIDN O J,SERBEST E.New experimental results on transpiration cooling for hydrogen/oxygen rocket combustion chambers[R].Cleveland,Ohio,US:the 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,1998.
    [31]
    MAY L,BURKHARDT W M.Transpiration cooled throat for hydrocarbon rocket engines[R].National Aeronautics and Space Administration,NASA-CR-184272,1991.
    [32]
    ZHU Yinhai,JIANG Peixue,SUN Jiguo,et al.Injector head transpiration cooling coupled with combustion in H2/O2 subscale thrust chamber[J].Journal of Thermophysics and Heat Transfer,2013,27(1):42-51.
    [33]
    李青,孙纪国.多孔陶瓷氢气发汗冷却特性研究[J].推进技术,2014,10(10):1387-1391.
    [34]
    CHEN F,BOWMAN W J,BOWERSOX R.Effect of transpiration cooling on nozzle heat transfer[J].Journal of Spacecraft and Rockets,1996,33(3):453-455.
    [35]
    MOFFAT R J,KAYS M W.The turbulent boundary layer on a porous plate:experimental heat transfer with uniform blowing and suction[J].International Journal of Heat and Mass Transfer,1968,11(10):1547-1566.
    [36]
    FOGAROLI R P,SAYDAH A R.Turbulent heat transfer and skin friction measurements on a porous cone with air injection[J].AIAA Journal,1966,4(6):1116-1117.
    [37]
    BARTLE E R,LEADON B M.The effectiveness as a universal measure of mass transfer cooling for a turbulent boundary layer[M].Palo Alto,US:Stanford University Press,1962.
    [38]
    RANNIE W D.A simplified theory of porous wall cooling[R].Pasadena,California,US:National Aeronautics and Space Administration,1947.
    [39]
    LAGANELLI L.Comparison between film cooling and transpiration cooling system in high speed flow[R].New York,US:the 8th Aerospace Sciences Meeting,1970.
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