两种燃烧加热风洞参数匹配方案的比较

推进技术 ›› 2017, Vol. 38 ›› Issue (6): 1226-1234.

两种燃烧加热风洞参数匹配方案的比较

刘坤伟¹,朱雨建¹,杨基明¹,毛雄兵²,吴颖川²

中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国科学技术大学近代力学系，安徽合肥 230027,中国空气动力研究与发展中心，四川绵阳 621000,中国空气动力研究与发展中心，四川绵阳 621000

发布日期:2021-08-15
作者简介:刘坤伟，男，博士生，研究领域为超声速空气动力学。E-mail: lkw2011@mail.ustc.edu.cn 通讯作者:朱雨建，男，副研究员，研究领域为空气动力学、激波。
基金资助:
国家自然科学基金(11132010；11402263)。

Comparison of Two Typical Flow-Parameter-Matching Schemes in a Combustion Wind Tunnel

Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,Department of Modern Mechanics，University of Science and Technology of China，Hefei 230027，China,China Aerodynamics Research and Development Center，Mianyang 621000，China and China Aerodynamics Research and Development Center，Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 燃烧加热风洞中的地面高超声速试验通常模拟真实飞行状态下的静温，静压，马赫数(TPM)或总焓，动压，马赫数(h0QM)。为弄清气流参数匹配方式对发动机性能的影响及其机理，基于准一维带化学反应数值模拟对这两种典型匹配方案获得可靠的燃烧室压力分布与发动机推力及比冲的能力进行了比较。结果表明，对于氢燃料加热气流，若燃烧室内未出现明显的局部热壅塞引起的激波结构，TPM匹配方案能较好模拟纯空气流动当量比相同时的压力分布；h0QM匹配方案则能更好模拟燃料量相同的情况；对于模拟燃烧室热壅塞效应，h0QM匹配方案表现更好。从模拟发动机推力的角度来说，两种匹配方案均可通过调整燃油量达到与纯空气结果的较好契合，不管燃烧室内是否出现壅塞激波结构；从模拟燃料比冲的角度来说，则h0QM匹配方案更可靠。燃烧释热比不同是导致两种匹配方案表现不同的关键原因。对于酒精燃料加热气流，两种匹配方案下发动机性能相仿；但此时污染效应更强，给优化匹配方案以准确模拟发动机性能带来更多挑战。

关键词: 燃烧加热风洞；污染；匹配方案；准一维数值模拟

Abstract: Either the “static temperature + static pressure + flow Mach number (TPM)” or the “total enthalpy + dynamic pressure + flow Mach number (h0QM)” of the real fight conditions is generally simulated in ground-based hypersonic testing in a combustion wind tunnel. To clarify their influence mechanisms on the performance of a scramjet engine，the two typical sets of freestream parameter matching schemes were compared based on quasi-one-dimensional numerical simulation with chemical reaction，in respect of their capability of reliably reproducing the pressure distribution along the combustor and the thrust as well as the specific impulse the engine generates. It was found that for the hydrogen-vitiated flow，it is easier to select the TPM-matched scheme for identical fuel equivalence ratio and the h0QM-matched scheme for identical fuel mass flow rate，to better reproduce the combustor pressure distribution in real flight，if no local thermal-choking-induced shock structure is evident in the combustor. If thermal choking is likely to occur，the h0QM-matched scheme could reproduce the flow pattern more reliably. For the thrust of the engine，good agreement with that in clean air could be achieved by adjusting the fuel mass flow rate for both the two matching schemes，whether or not there is a shock in the combustor. To obtain a reliable fuel-based specific impulse，however，it seems the h0QM-matched scheme is a more appropriate choice. The disparity of combustion heat release ratio in the two matching schemes contributes heavily to the aforementioned differences. For the alcohol-vitiated flow，the engine performance appear nearly the same in the two matching schemes. In this case，the vitiation effect is aggravated so that it is more difficult to reliably reproduce the engine performance by adjusting the freestream parameters.

Key words: Combustion wind tunnel；Vitiation；Matching scheme；Quasi-one-dimensional numerical simulation

刘坤伟,朱雨建,杨基明,毛雄兵,吴颖川. 两种燃烧加热风洞参数匹配方案的比较[J]. 推进技术, 2017, 38(6): 1226-1234.

LIU Kun-wei¹,ZHU Yu-jian¹,YANG Ji-ming¹,MAO Xiong-bing²,WU Ying-chuan². Comparison of Two Typical Flow-Parameter-Matching Schemes in a Combustion Wind Tunnel[J]. Journal of Propulsion Technology, 2017, 38(6): 1226-1234.

参考文献

[1] Edelman R B, Spadaccini L J. Theoretical Effects of Vitiated Air Contamination on Ground Testing of Hypersonic Airbreathing Engines[J]. Journal of Spacecraft and Rockets, 1969, 6(12): 1442-1447.
[2] Tirres C, Bradley M, Morrison C, et al. A Flow Quality Analysis for Future Hypersonic Vehicle Testing [R]. AIAA 2002-2706.
[3] Boyce R R, Paull A, Stalker R J, et al. Comparison of Supersonic Combustion between Impulse and Vitiation-Heated Facilities [J]. Journal of Propulsion and Power, 2000, 16(4): 709-717.
[4] Boyce R R, Wendt M, Paull A, et al. Supersonic Combustion-a Shock Tunnel and Vitiation-Heated Blowdown Tunnel Comparison [R]. AIAA 98-0941.
[5] Mitani T, Hiraiwa T, Sato S, et al. Comparison of Scramjet Engine Performance in Mach 6 Vitiated and Storage-Heated Air [J]. Journal of Propulsion and Power, 1997, 13(5): 635-642.
[6] Mitani T, Hiraiwa T, Sato S, et al. Scramjet Engine Testing in Mach 6 Vitiated Air [R]. AIAA 96-4555.
[7] Hiraiwa T, Sato S, Tomioka S, et al. Testing of a Scramjet Engine Model in Mach 6 Vitiated Air Flow [R]. AIAA 97-0292.
[8] Rockwell R D, Goyne C P, Haw W L, et al. Experimental Study of Test-Medium Vitiation Effects on Dual-Mode Scramjet Performance[J]. Journal of Propulsion and Power, 2011, 27(5): 1135-1142.
[9] Krauss R H, Gauba G, Whitehurst R B, et al. Experimental and Numerical Investigation on Steam-Vitiated Supersonic Hydrogen Combustion [R]. AIAA 96-0856.
[10] Haw W L, Goyne C P, Rockwell R D, et al. Experimental Study of Vitiation Effects on Scramjet Mode Transition[J]. Journal of Propulsion and Power, 2011, 27(2): 506-509.
[11] McDaniel J C, Krauss R H, Whitehurst W B, et al. Test Gas Vitiation Effects in a Dual-Mode Combustor [R]. AIAA 2003-6960.
[12] Goyne C P, McDaniel J C, Krauss R H, et al. Test Gas Vitiation Effects in a Dual-Mode Scramjet Combustor [J]. Journal of Propulsion and Power, 2007, 23(3): 559-565.
[13] Rockwell R D, Goyne C P, Haw W L, et al. Experimental Study of Test Medium Vitiation Effects on Dual-Mode Scramjet Mode Transition[R]. AIAA 2010-1126.
[14] Srinivasan S, Erickson W D. Interpretation of Vitiation Effects on Testing at Mach 7 Flight Conditions[R]. AIAA 95-2719.
[15] 王磊, 宋文艳, 罗飞腾. H2O组分对氢燃料超音速燃烧室性能的影响[J]. 航空工程进展, 2010, 1(2): 159-163.
[16] 张志强, 宋文艳, 罗飞腾. H2O/CO₂ 组分对氢和乙烯超声速燃烧室性能影响数值模拟 [J]. 西北工业大学学报, 2012, 30(2): 256-261.
[17] Luo F, Song W, Zhang Z, et al. Experimental and Numerical Studies of Vitiated Air Effects on Hydrogen-Fueled Supersonic Combustor Performance[J]. Chinese Journal of Aeronautics, 2012, 25(2): 164-172.
[18] 陈亮, 宋文艳, 罗飞腾. H2O/CO₂污染对煤油燃料双模态超声速燃烧室影响研究[J]. 推进技术, 2015, 36(2): 253-260. (CHEN Liang, SONG Wen-yan, LUO Fei-teng. Vitiation Effects of H2O/CO₂ on Kerosene-Fueled Dual-Mode Supersonic Combustor Performance [J]. Journal of Propulsion Technology, 2015, 36(2): 253-260.)
[19] 刘伟雄, 杨阳, 邵菊香, 等. 空气污染组分H2O和CO₂对乙烯燃烧性能的影响[J]. 物理化学学报, 2009, 25(8): 1618-1622.
[20] 邵菊香, 谈宁馨, 刘伟雄, 等. 空气污染组分H2O和CO₂对乙烯燃烧性能的影响(II)—反应机理和动力学模拟[J]. 物理化学学报, 2010, 26(2): 270-276.
[21] 刘伟雄, 贺伟, 李宏斌, 等. 污染组分对氢燃料发动机燃烧动力学的影响[J]. 科学通报, 2008, 53(18): 2257-2260.
[22] 侯凌云, 杨缙, 马雪松, 等. 空气污染各组分对甲烷超声速燃烧性能的影响[J]. 物理化学学报, 2010, 26(12): 3150-3156.
[23] 谭宇, 焦伟, 任虎. 不同燃烧加热方式风洞对超燃冲压发动机性能影响试验研究[C]. 厦门:第五届冲压发动机技术交流会, 2015.
[24] Oran E S, Weber W J, Stefaniw E I, et al. A Numerical Study of Two-Dimensional H2-O₂-Ar Detonation Using a Detailed Chemical Reaction Model[J]. Combustion and Flame, 1998, 113(1): 147-163.
[25] Kee R J, Rupley F M, Meeks E, et al. CHEMKIN-III: A Fortran Chemical Kinetics Package for the Analysis of Gas-Phase Chemical and Plasma Kinetics[R]. Sandia National Laboratory Report, SAND 96-8216, 1996.
[26] Kong S, Marriott C, Reitz R, et al. Modeling and Experiments of HCCI Engine Combustion Using Detailed Chemical Kinetics with Multidimensional CFD[R]. SAE Technical Paper 2001-01-1026, 2001.
[27] Rodriguez C G, Andrew D C. Computational Simulation of a Supersonic-Combustion Benchmark Experiment [R]. AIAA 2005-4424.
[28] Rodriguez C G, Cutler A D. Numerical Analysis of the SCHOLAR Supersonic Combustor[R]. NASA/CR-2003-212689.
[29] Tourani C. Computational Simulation of Scramjet Combustors - a Comparison between Quasi-One Dimensional and 2-D Numerical Simulation [D]. USA: University of Kansas School of Engineering, 2011.
[30] Liu K, Zhu Y, Gao W, et al. Influence of Combustion-Preheating Vitiation on Operablity of a Hypersonic Inlet [J]. Shock Waves, 2015, 25(1).(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2016-02-02；修订日期:2016-04-13。基金项目:国家自然科学基金(11132010；11402263)。作者简介:刘坤伟,男,博士生,研究领域为超声速空气动力学。E-mail: lkw2011@mail.ustc.edu.cn通讯作者:朱雨建,男,副研究员,研究领域为空气动力学、激波。E-mail: yujianrd@ustc.edu.cn