RBCC引射火箭燃烧室设计及试验研究 *

推进技术 ›› 2014, Vol. 35 ›› Issue (10): 1378-1386.

RBCC引射火箭燃烧室设计及试验研究 *

朱韶华¹,田　亮¹,刘亚冰²,侯金丽²,李　轩¹,徐　旭¹

北京航空航天大学宇航学院，北京 100191;北京航空航天大学宇航学院，北京 100191;中国航天科工集团三十一研究所，北京 100074;中国航天科工集团三十一研究所，北京 100074;北京航空航天大学宇航学院，北京 100191;北京航空航天大学宇航学院，北京 100191

发布日期:2021-08-15
作者简介:朱韶华(1990—)，男，博士生，研究领域为超燃冲压发动机技术。

Design and Experimental Investigation of Ejector Rocket Chamber for RBCC Propulsion System

School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100191，China;School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100191，China;The 31st Research Institute of CASIC，Beijing 100074，China;The 31st Research Institute of CASIC，Beijing 100074，China;School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100191，China;School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为了满足RBCC推进系统需求，进行了气氧/煤油引射火箭燃烧室的设计和试验研究。燃烧室室压为2MPa，氧燃比为1.6，火箭流量在95~285g/s范围内变化。通过火箭单独的冷、热态试验，对其流量控制、点火、喷注及面板和身部热防护进行了考核验证，均得到了较满意的结果。在此基础上研究了RBCC联试中火箭燃烧室的工作性能，试验结果表明:燃烧室的特征速度燃烧效率能达到88%~98%，且受到流量、氧燃比、动量通量比和喷注压降的影响较大，在适合的范围内选取大的动量通量比和喷注压降，能得到更好的雾化、掺混及燃烧性能；气氧/煤油的内直外旋喷嘴构型在煤油压降仅为设计点的11%时，仍能通过有效的气动作用，获得88%以上的特征速度燃烧效率；点火器的吹除气在占到火箭流量5%时，会造成燃烧室3%的性能损失，需要在试验中进行控制并在性能计算时予以考虑。在对火箭单试和联试的比较中发现，联试中由于其特征长度长燃烧更充分，火箭得到了近7%的特征速度燃烧效率增长。

关键词: 火箭基组合循环；气氧/煤油；氧燃比

Abstract: A GO₂/kerosene ejector rocket chamber was designed and tested to meet the requirements of the RBCC propulsion system. It was required to operate at chamber pressure 2MPa and 1.6 mixture ratio，while the mass flow rate of the rocket was changed from 95g/s to 285g/s. The mass flow rate controlling，ignition，injection and thermal protection of the faceplate and chamber body have achieved reasonably good performance during the reacting flow tests and non-reacting flow tests. Then the performance of the rocket was investigated in the RBCC combined tests. As the results shown，the rocket has achieved efficiency 88%~98% C*，and it is influenced by the mass flow rate，mixture ratio，momentum flux ratio and pressure decrease of the rocket. The higher momentum flux ratio and pressure decrease in a suitable range，the better performance of the atomizing，mixing and burning will attain. Although the pressure decrease of the kerosene is only 11% of the design value，the GO₂/kerosene Gas Center Swirl Coaxial (GCSC) injector can achieve efficienicy at least 88% C* by effective aerodynamic effects. The purge flow should be controlled in tests and taken into account when the performance of the rocket is analyzed，as there will be efficiency decrease by 3% C* when the purge flow reaches 5% of the rocket mass flow rate. When the performance of the rocket is compared in the separate tests and combined tests，the rocket is found to attain almost efficiency 7% higher C* in combined test，because of its longer characteristic length.

Key words: RBCC；GO₂/Kerosene；Mixture ratio

朱韶华,田　亮,刘亚冰,侯金丽,李　轩,徐　旭. RBCC引射火箭燃烧室设计及试验研究 *[J]. 推进技术, 2014, 35(10): 1378-1386.

ZHU Shao-hua¹,TIAN Liang¹,LIU Ya-bing²,HOU Jin-li²,LI Xuan¹,XU Xu¹. Design and Experimental Investigation of Ejector Rocket Chamber for RBCC Propulsion System[J]. Journal of Propulsion Technology, 2014, 35(10): 1378-1386.

参考文献

[1] Siebenhaar A, Bulman M J, Bonnar D K.The Role of the Strut Jet Engine in New Global and Space Markets[R].IAF-98-S.5.04.
[2] Adam Siebenhaar, Mel Bulman.The Strut Jet Engine the Over Looked Option for Space Launch[R].AIAA 95-3124.
[3] Uwe Hueter , Jim Turner.Rocket Based Combined Cycle Activities in the Advanced Space Transportation Program Office[R].AIAA 99-2353.
[4] Neill T M, Gladstone J D.Durability Demonstration of Small High Performance Rocket Thrusters for RLV Applications[R].AIAA 99-2357.
[5] Santoro R J, Pal S, Woodward R D, et al.Rocket Testing at University Facilities[R].AIAA 2001-0748.
[6] Faulkner Robert F.Integrated System Test of an Airbreathing Rocket (ISTAR)[R].AIAA 2001-1812.
[7] Jason Eugene Quinn.Oxidizer Selection for The ISTAR Program (Liquid Oxygen Versus Hydrogen Peroxide)[R].AIAA 2002-4206.
[8] Masao Takegoshi, SadatakeTomioka, Shuichi Ueda, et al. Firing-Tests of a Rocket Combustor for Combined Cycle Engine at Various Conditions[R].AIAA 2005-4286.
[9] Masao Takegoshi, SadatakeTomioka, Shuichi Ueda, et al. Performances of a Rocket Chamber for the Combined-cycle Engine at Various Conditions[R].AIAA 2006-7978.
[10] Masao Takegoshi, SadatakeTomioka, Fumiei Ono, et al.Injiectors and Combustion Performance of Rocket Thruster for Rocket-Ramjet Combined-Cycle Engine Model[R]. AIAA 2012-5915.
[11] 刘永兴, 王魁, 曹再勇. RBCC推进系统主火箭发动机气氧/煤油推力室研究[J].火箭推进, 2009, 35(6).
[12] 彭丽娜. RBCC主火箭与燃烧室热防护分析与试验[D]. 西安: 西北工业大学, 2007.
[13] 蔡国飙, 李家文, 田爱梅, 等. 液体火箭发动机设计[M]. 北京:北京航空航天大学出版社, 2011: 75-220.
[14] 杜正刚, 金平, 杨立军, 等. 气气喷注器流量特性试验研究[J].航空动力学报, 2007, 22(3).
[15] 高玉闪, 金平, 蔡国飙. 气氧/甲烷与气氢/气氧喷注器燃烧特性对比研究[J].推进技术, 2013, 34(6):775-780.(GAO Yu-shan, JIN Ping, CAI Guo-biao.Comparison of Combustion Characteristics for GO₂/CH4 and GH2/CO₂ Injectors [J].Journal of Propulsion Technology, 2013, 34(6): 775-780.)
[16] 李宜敏, 张中钦, 张远君, 等. 固体火箭发动机原理[M].北京: 北京航空航天大学出版社, 1992.
[17] Sanford Gordon, Bonnie J, McBride. Computer Program for Calculation of Complex Chemical Equilibrium Compositions and Applications[R].NASA RP-1311.
[18] JaehyongJeonMoongeun Hong, Yeoung-Min Han, Soo Yong Lee.Experimental Study on Spray Characteristics of Gas-Centerd Swirl Coaxial Injectors[J].Journal of Fluids Engineering,2011, 133(12).
[19] 汪小卫. 气气燃烧与气气喷注器技术研究[D]. 北京:北京航空航天大学研究生院, 2011.(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2013-10-08；修订日期:2013-11-28。作者简介:朱韶华(1990—),男,博士生,研究领域为超燃冲压发动机技术。E-mail:zhushaohua@sa.buaa.edu.cn