RBCC发动机超燃/火箭模式流场数值模拟研究

推进技术 ›› 2013, Vol. 34 ›› Issue (12): 1643-1649.

RBCC发动机超燃/火箭模式流场数值模拟研究

汤祥,何国强,秦飞

西北工业大学燃烧、热结构与内流场重点实验室,陕西西安 710072;西北工业大学燃烧、热结构与内流场重点实验室,陕西西安 710072;西北工业大学燃烧、热结构与内流场重点实验室,陕西西安 710072

发布日期:2021-08-15
作者简介:汤祥(1987—),男,博士生,研究领域为航空宇航推进理论与工程。E-mail:tangxiang--050434@163.com

Numerical Simulations on RBCC Engine in Scramjet/Rocket Mode

Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory, Northwestern Polytechnical University, Xi’an 710072, China;Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory, Northwestern Polytechnical University, Xi’an 710072, China;Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory, Northwestern Polytechnical University, Xi’an 710072, China

Published:2021-08-15

摘要/Abstract

摘要： 针对进排气系统与燃烧室匹配工作的中心支板式火箭基组合动力循环(RBCC)发动机,通过数值模拟研究了RBCC发动机在低动压、高速高空域飞行条件下以超燃/火箭模式工作时的燃烧流场特征,并分析了支板火箭喷管出口流量的变化对燃烧流场的影响。结果表明:在超燃/火箭模式下,支板火箭工作能促进燃料与空气的掺混燃烧,实现发动机稳定工作,同时可提升发动机的推力性能；随着支板火箭流量的增加,发动机产生的总推力逐渐增大,总推力与火箭流量大小近似成正比；随着火箭流量的增加,燃烧室中的流动状态向以超声速流动占主导地位发展,进气道的抗反压能力得到提升。 

关键词: 火箭基组合动力循环;超燃/火箭;支板火箭;流量;数值模拟 

Abstract: Under the conditions of low dynamic pressure, high velocity and high flight altitude, numerical simulations were carried out to analyze the flowfield characteristics of rocket-based combined cycle (RBCC) engine in the Scramjet/rocket mode, which was composed of a combustor matched with an appropriate inlet and exhaust system. The effects of the variations of the strut-rocket mass flowrate at the exit of the nozzle on the combustion flow were also investigated. The results show that in Scramjet/rocket mode, the operation of strut-rocket can enhance the mixing and combustion between fuel and air, realize the steady operation of engine, while promoting the thrust performance. The total thrust of the engine increases gradually with the increment of the strut-rocket mass flowrate, which is proportional to the rocket mass flowrate approximately. The flow condition in the combustor develops towards the flow dominated by supersonic, and the resistance pressure ability of the inlet improves as the rocket flowrate increases. 

Key words: Rocket-based combined cycle; Scramjet/Rocket; Strut-rocket; Mass flow; Numerical simulation

汤祥,何国强,秦飞. RBCC发动机超燃/火箭模式流场数值模拟研究[J]. 推进技术, 2013, 34(12): 1643-1649.

TANG Xiang, HE Guo-qiang, QIN Fei. Numerical Simulations on RBCC Engine in Scramjet/Rocket Mode[J]. Journal of Propulsion Technology, 2013, 34(12): 1643-1649.

参考文献

[1] Russell Daines, Corin Segal.Combined Rocket and Airbreathing Propulsion Systems for Space-Launch Applications[J].Journal of Propulsion and Power, 1998,4(5):605-612.
[2] Takeshi Kanda, Kouichiro Tani, Kenji Kudo.Conceptual Study of a Rocket-Ramjet Combined-Cycle Engine for an Aerospace Plane[J].Journal of Propulsion and Power, 2007,3(2):301-309.
[3] 秦飞, 吕翔, 刘佩进, 等.火箭基组合推进研究现状与前景[J].推进技术, 2010,1(6):660-665.(QIN Fei, LV Xiang, LIU Pei-jin, et al.Research Status and Perspective of Rocket Based Combined Cycle Propulsion System[J].Journal of Propulsion Technology, 2010,1(6):660-665.)
[4] 潘科玮, 何国强, 秦飞, 等.用小支板及凹腔组合提高火箭冲压组合发动机的燃烧性能[J].推进技术, 2012,3(2):216-220.(PAN Ke-wei, HE Guo-qiang, QIN Fei, et al.Combustion Performance of RBCC Engine with Pylon and Cavity at Ramjet Mode[J].Journal of Propulsion Technology, 2012,3(2):216-220.)
[5] 潘科玮.RBCC亚燃模态燃烧组织及燃油喷注规律研究[D].西安:西北工业大学, 2012.
[6] 何国强, 徐朝启, 秦飞, 等.基于直扩流道构型的RBCC发动机亚燃模态高效燃烧组织研究[J].推进技术, 2013,4(8):1064-1070.(HE Guo-qiang, XU Chao-qi, QIN Fei, et al.Research on Ramjet-Mode Combustion Organization Based on Constant-Expansion Area Configuration in RBCC Combustor[J].Journal of Propulsion Technology, 2013,4(8):1064-1070.)
[7] 徐朝启, 何国强, 刘佩进, 等.RBCC发动机亚燃模态一次火箭引导燃烧的实验[J].航空动力学报, 2013,8(3):567-571.
[8] 李鹏飞.RBCC超燃模态数值模拟与试验研究[D].西安:西北工业大学, 2011.
[9] Karl William Nelson.Experimental Investigation of an Ejector Scramjet RBCC at Mach 4.0and 6.5Simulated Flight Conditions[D].Huntsville:Engineering/ Mechanical &Aerospace Engineering, 2002.
[10] Nelson K W, Hawk C W.Experimental Investigation of an Integrated Strut-Rocket/Scramjet Operating at Mach 4.0and 6.5Conditions[C].Cleveland:JANNAF Propulsion Meeting, 1998.
[11] Kanenori Kato, Takeshi Kanda, Kenji Kudo, et al.Mach-8Tests of a Combined-Cycle Engine Combustor[J].Journal of Propulsion and Power, 2007,3(5):1018-1022.
[12] Bulman Mel, Neil Todd, Yam Clement.Strutjet RBCC Engine Performance[C].Los Angeles:Joint Propulsion, 1999.
[13] 张蒙正, 李斌, 王君, 等.关于RBCC动力系统的思考[J].火箭推进, 2013,9(1):1-7.
[14] 张浩.RBCC发动机变几何进气道和尾喷管研究[D].西安:西北工业大学, 2013.
[15] 潘科玮, 何国强, 秦飞, 等.煤油燃料RBCC亚燃模态掺混与燃烧数值模拟研究[J].推进技术, 2012,3(6):907-913.(PAN Ke-wei, HE Guo-qiang, QIN Fei, et al.Study on Mixing and Combustion of Kerosene Fuel in Ramjet Mode of RBCC Engine[J].Journal of Propulsion Technology, 2012,3(6):907-913.)