CLC number:
On-line Access: 2024-08-20
Received: 2023-07-16
Revision Accepted: 2023-10-24
Crosschecked: 2024-08-20
Cited: 0
Clicked: 915
Xinlin LIU, Jun SUN, Zhuohang JIANG, Qinglian LI, Peng CHENG, Jie SONG. Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine[J]. Journal of Zhejiang University Science A, 2024, 25(8): 631-649.
@article{title="Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine",
author="Xinlin LIU, Jun SUN, Zhuohang JIANG, Qinglian LI, Peng CHENG, Jie SONG",
journal="Journal of Zhejiang University Science A",
volume="25",
number="8",
pages="631-649",
year="2024",
publisher="Zhejiang University Press & Springer",
doi="10.1631/jzus.A2300365"
}
%0 Journal Article
%T Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine
%A Xinlin LIU
%A Jun SUN
%A Zhuohang JIANG
%A Qinglian LI
%A Peng CHENG
%A Jie SONG
%J Journal of Zhejiang University SCIENCE A
%V 25
%N 8
%P 631-649
%@ 1673-565X
%D 2024
%I Zhejiang University Press & Springer
%DOI 10.1631/jzus.A2300365
TY - JOUR
T1 - Gas film/regenerative composite cooling characteristics of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine
A1 - Xinlin LIU
A1 - Jun SUN
A1 - Zhuohang JIANG
A1 - Qinglian LI
A1 - Peng CHENG
A1 - Jie SONG
J0 - Journal of Zhejiang University Science A
VL - 25
IS - 8
SP - 631
EP - 649
%@ 1673-565X
Y1 - 2024
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/jzus.A2300365
Abstract: The thermal protection of rocket engines is a crucial aspect of rocket engine design. In this paper, the gas film/regenerative composite cooling of the liquid oxygen/liquid methane (LOX/LCH4) rocket engine thrust chamber was investigated. A gas film/regenerative composite cooling model was developed based on the Grisson gas film cooling efficiency formula and the one-dimensional regenerative cooling model. The accuracy of the model was validated through experiments conducted on a 6 kg/s level gas film/regenerative composite cooling thrust chamber. Additionally, key parameters related to heat transfer performance were calculated. The results demonstrate that the model is sufficiently accurate to be used as a preliminary design tool. The temperature rise error of the coolant, when compared with the experimental results, was found to be less than 10%. Although the pressure drop error is relatively large, the calculated results still provide valuable guidance for heat transfer analysis. In addition, the performance of composite cooling is observed to be superior to regenerative cooling. Increasing the gas film flow rate results in higher cooling efficiency and a lower gas-side wall temperature. Furthermore, the position at which the gas film is introduced greatly impacts the cooling performance. The optimal introduction position for the gas film is determined when the film is introduced from a single row of holes. This optimal introduction position results in a more uniform wall temperature distribution and reduces the peak temperature. Lastly, it is observed that a double row of holes, when compared to a single row of holes, enhances the cooling effect in the superposition area of the gas film and further lowers the gas-side wall temperature. These results provide a basis for the design of gas film/regenerative composite cooling systems.
[1]AliMS, AnwarZ, MujtabaMA, et al., 2021. Two-phase frictional pressure drop with pure refrigerants in vertical mini/micro-channels. Case Studies in Thermal Engineering, 23:100824.
[2]BertschSS, GrollEA, GarimellaSV, 2008. Refrigerant flow boiling heat transfer in parallel microchannels as a function of local vapor quality. International Journal of Heat and Mass Transfer, 51(19-20):4775-4787.
[3]CaryAM, HefnerJN, 1972. Film-cooling effectiveness and skin friction in hypersonic turbulent flow. AIAA Journal, 10(9):1188-1193.
[4]DannenbergRE, 1962. Helium Film Cooling on a Hemisphere at a Mach Number of 10. Technical Report No. NASA TN D-1550, NASA Ames Research Center, Moffett Field, USA.
[5]GaoXF, ZhangJW, SunB, et al., 2018. Study on optimal gas film parameters of near-injection region in thrust chamber. Journal of Rocket Propulsion, 44(2):10-17 (in Chinese).
[6]GoldsteinRJ, 1971. Film cooling. Advances in Heat Transfer, 7:321-379.
[7]GoldsteinRJ, EckertERG, TsouFK, et al., 1966. Film cooling with air and helium injection through a rearward-facingslot into a supersonic air flow. AIAA Journal, 4(6):981-985.
[8]GradlPR, ProtzCS, 2020. Technology advancements for channel wall nozzle manufacturing in liquid rocket engines. Acta Astronautica, 174:148-158.
[9]GururatanaS, PrapainopR, ChuepengS, et al., 2021. Development of heat transfer performance in tubular heat exchanger with improved NACA0024 vortex generator. Case Studies in Thermal Engineering, 26:101166.
[10]HaoJH, ChenQ, LiX, et al., 2021. A correction factor-based general thermal resistance formula for heat exchanger design and performance analysis. Journal of Thermal Science, 30(3):892-901.
[11]HeuferKA, OlivierH, 2006. Film cooling of an inclined flat plane in hypersonic flow. The 14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference, p.1-14.
[12]HongY, LiuZY, SilvestriS, et al., 2019. An experimental and modelling study of heat loads on a subscale methane rocket motor. Acta Astronautica, 164:112-120.
[13]HowardFG, SrokowskiAJ, 1977. Cooling effectiveness of slot injection into a turbulent boundary layer. AIAA Journal, 15(9):1366-1368.
[14]HuzelDK, HuangDH, 1992. Modern Engineering for Design of Liquid-Propellant Rocket Engines. American Institute of Aeronautics and Astronautics, Washington, USA, p.147.
[15]JagannathanR, ElliottM, JohansenC, et al., 2018. Study of heat transfer with surface treatment in pre-coolers for aeroengine applications. Case Studies in Thermal Engineering, 12:742-748.
[16]KandaT, MasuyaG, OnoF, et al., 1994. Effect of film cooling/regenerative cooling on scramjet engine performances. Journal of Propulsion and Power, 10(5):618-624.
[17]KellerMA, KlokerMJ, 2017. Direct numerical simulation of foreign-gas film cooling in supersonic boundary-layer flow. AIAA Journal, 55(1):99-111.
[18]KellerMA, KlokerMJ, OlivierH, 2015. Influence of cooling-gas properties on film-cooling effectiveness in supersonic flow. Journal of Spacecraft and Rockets, 52(5):1443-1455.
[19]KonopkaM, MeinkeM, SchröderW, 2012. Large-eddy simulation of shock/cooling-film interaction. AIAA Journal, 50(10):2102-2114.
[20]LiGC, GaoZY, ZhangW, et al., 2019. Effects of combination of forward jet and backward jet with two rows of holes on film cooling. Journal of Propulsion Technology, 40(3):643-652 (in Chinese).
[21]LiMC, WeiSS, HuangCH, et al., 2022. Experimental and numerical investigation of swirling H2O2 and polypropylene hybrid rocket motor with regenerative cooling. Acta Astronautica, 190:283-298.
[22]LiangT, SongJ, LiQL, et al., 2021. System scheme design of electric expander cycle for LOX/LCH4 variable thrust liquid rocket engine. Acta Astronautica, 186:451-464.
[23]LiangT, XuWW, YeW, et al., 2023. Study on the heat transfer characteristics of a plate-fin-typed precooler considering cooling fluid phase change. Case Studies in Thermal Engineering, 47:103073.
[24]LushchikVG, YakubenkoAE, 2001. Tangential-slot film cooling on a plate in supersonic flow. Comparison of calculation and experiment. Fluid Dynamics, 36(6):926-933.
[25]MetzgerDE, CarperHJ, SwankLR, 1968. Heat transfer with film cooling near nontangential injection slots. Journal of Engineering for Power, 90(2):157-162.
[26]MiaoHY, WangZW, NiuYB, 2020a. Performance analysis of cooling system based on improved supercritical CO2 Brayton cycle for scramjet. Applied Thermal Engineering, 167:114774.
[27]MiaoHY, WangZW, NiuYB, 2020b. Key issues and cooling performance comparison of different closed Brayton cycle based cooling systems for scramjet. Applied Thermal Engineering, 179:115751.
[28]PengW, JiangPX, 2009. Influence of shock waves on supersonic film cooling. Journal of Spacecraft and Rockets, 46(1):67-73.
[29]PengW, SunXK, JiangPX, et al., 2017. Effect of continuous or discrete shock wave generators on supersonic film cooling. International Journal of Heat and Mass Transfer, 108:770-783.
[30]PerakisN, HaidnOJ, 2020. Wall heat transfer prediction in CH4/O2 and H2/O2 rocket thrust chambers using a non-adiabatic flamelet model. Acta Astronautica, 174:254-269.
[31]PhuNM, HapNV, 2020. Influence of inlet water temperature on heat transfer and pressure drop of dehumidifying air coil using analytical and experimental methods. Case Studies in Thermal Engineering, 18:100581.
[32]PizzarelliM, 2021. Overview and analysis of the experimentally measured throat heat transfer in liquid rocket engine thrust chambers. Acta Astronautica, 184:46-58.
[33]PizzarelliM, NasutiF, OnofriM, 2014. Effect of cooling channel aspect ratio on rocket thermal behavior. Journal of Thermophysics and Heat Transfer, 28(3):410-416.
[34]RuanB, HuangSZ, MengH, et al., 2017. Transient responses of turbulent heat transfer of cryogenic methane at supercritical pressures. International Journal of Heat and Mass Transfer, 109:326-335.
[35]SongJ, LiangT, LiQL, et al., 2021. Study on the heat transfer characteristics of regenerative cooling for LOX/LCH4 variable thrust rocket engine. Case Studies in Thermal Engineering, 28:101664.
[36]SunB, ZhangJW, 2016. Thermal Protection Technology of Rocket Engine. Beihang University Press, Beijing, China, p.84-112 (in Chinese).
[37]SunB, YangW, ZhengLM, et al., 2013. Numerical simulation of liquid film and regenerative cooling in a rocket combustor. Journal of Aerospace Power, 28(6):1357-1363 (in Chinese).
[38]TakitaK, MasuyaG, 2000. Effects of combustion and shock impingement on supersonic film cooling by hydrogen. AIAA Journal, 38(10):1899-1906.
[39]ThomeJR, ConsoliniL, 2010. Mechanisms of boiling in micro-channels: critical assessment. Heat Transfer Engineering, 31(4):288-297.
[40]TrejoA, GarciaC, ChoudhuriA, 2016. Experimental investigation of transient forced convection of liquid methane in a channel at high heat flux conditions. Experimental Heat Transfer, 29(1):97-112.
[41]WanH, YuanB, QinF, et al., 2020. Numerical simulation of composite cooling of RBCC ejector rocket using gradient micro-channels. Journal of Engineering Thermophysics, 41(5):1179-1185 (in Chinese).
[42]Waxenegger-WilfingGW, DresiaK, DeekenJC, et al., 2020. Heat transfer prediction for methane in regenerative cooling channels with neural networks. Journal of Thermophysics and Heat Transfer, 34(2):347-357.
[43]YangW, SunB, 2013. Numerical simulation of liquid film and regenerative cooling in a liquid rocket. Applied Thermal Engineering, 54(2):460-469.
[44]YangXB, BadcockKJ, RichardsBE, et al., 2003. Numerical simulation of film cooling in hypersonic flows. The 36th AIAA Thermophysics Conference, p.1-7.
[45]YangXB, BadcockKJ, RichardsBE, et al., 2005. A numerical study of hypersonic turbulent film cooling. The 43rd AIAA Aerospace Sciences Meeting and Exhibit, p.1-15.
[46]YuWL, ZhouWX, JiaZJ, et al., 2022. Characteristics of scramjet regenerative cooling with endothermic chemical reactions. Acta Astronautica, 195:1-11.
[47]ZengM, LiuW, ZouJJ, 2016. Fundamentals of Aerodynamics. Science Press, Beijing, China, p.203-214 (in Chinese).
[48]ZhangBC, LiQL, WangY, et al., 2020. Experimental investigation of nitrogen flow boiling heat transfer in a single mini-channel. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 21(2):147-166.
[49]ZhangHW, HeYL, TaoWQ, 2007. Numerical study of film and regenerative cooling in a thrust chamber at high pressure. Numerical Heat Transfer, Part A: Applications, 52(11):991-1007.
[50]ZhangM, SunB, 2020. Effect of artificial roughness on flow and heat transfer of transcritical methane. International Journal of Thermal Sciences, 158:106528.
[51]ZhangSL, QinJ, XieKL, et al., 2016. Thermal behavior inside scramjet cooling channels at different channel aspect ratios. Journal of Propulsion and Power, 32(1):57-70.
[52]ZhangYL, 1984. State-space analysis of the dynamic characteristics of a variable thrust liquid propellant rocket engine. Acta Astronautica, 11(7-8):535-541.
[53]ZhangZL, ZhangMZ, ZhouLX, 2016. Liquid Rocket Engine Thermal Protection. National Defense Industry Press, Beijing, China(in Chinese).
[54]ZhouC, YuNJ, WangJ, et al., 2021. Analysis of dynamic characteristics and sensitivity of hydrogen-oxygen expansion cycle rocket engine system. Acta Astronautica, 189:624-637.
[55]ZhuNC, LiuGD, 2009. Liquid Rocket Engine Design. China Aerospace Press, Beijing, China, p.545 (in Chinese).
[56]ZuoJY, ZhangSL, QinJ, et al., 2018. Performance evaluation of regenerative cooling/film cooling for hydrocarbon fueled scramjet engine. Acta Astronautica, 148:57-68.
Open peer comments: Debate/Discuss/Question/Opinion
<1>