双燃烧室冲压发动机亚燃室设计与实验研究

推进技术 ›› 2013, Vol. 34 ›› Issue (1): 69-75.

双燃烧室冲压发动机亚燃室设计与实验研究

杨占宇,单鹏,郭德三,赵吕顺,介克,刘建

北京航空航天大学能源与动力工程学院,北京 100191;北京航空航天大学能源与动力工程学院,北京 100191;北京航空航天大学能源与动力工程学院,北京 100191;北京航空航天大学能源与动力工程学院,北京 100191;北京航空航天大学能源与动力工程学院,北京 100191;北京航空航天大学能源与动力工程学院,北京 100191

发布日期:2021-08-15
作者简介:杨占宇(1982—),男,博士生,研究领域为超声速燃烧实验及数值模拟。E-mail:yzy407@sohu.com
基金资助:
国家自然科学基金 (50076003);国家自然科学基金重大研究计划子课题(90305010)。

Design Improvement and Validation of Subsonic Combustor Pilot Burner for Dual Combustor Ramjet

College of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;College of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;College of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;College of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;College of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;College of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

Published:2021-08-15

摘要/Abstract

摘要： 在来流马赫数2.5,总温为285K的条件下,对于带亚燃预燃和流向涡掺混的超声速双燃烧室的亚燃室,进行了计算流体力学正问题设计研究以及实验验证研究。结果表明,亚燃室通过采用内压式三波系进气道、前部集中式主燃孔的火焰筒、增大了的亚燃室体积和火炬流喷口截面积、增设的V型火焰稳定器,使亚燃室内流场组织合理,解决了进气道的热态失速问题,得到了稳定的亚燃室燃烧和达到设计状态的火炬流喷射。 

关键词: 超声速流动;超声速燃烧;双燃室冲压发动机;预燃室;稳焰火炬

Abstract: Under the testbed condition of combustor inlet Mach number 2.5, total temperature 285K, this paper presents the design improvement with the numerical simulation of the cold flowfield and the experimental validation of the pilot burner of a direct-connected combined supersonic combustor with a streamwise vortices generator. The results indicate that, the design improvements, such as the triple-shock inlet, the burner liner with concentrated frontal holes, the pilot burner with a rather larger volume, the larger discharge-passage cross-sectional-area of the lobed mixer and the V-belt flame holder, rearrange the air distribution in the rectangular pilot burner and resolve the problem of the inlet stall during pre-combustion. The experiment obtains a stable pre-combustion and a torch plume achieving the design goal.

Key words: Supersonic flow; Supersonic combustion; Dual-combustor ramjet; Pilot burner; Flame holding torch

杨占宇,单鹏,郭德三,赵吕顺,介克,刘建. 双燃烧室冲压发动机亚燃室设计与实验研究[J]. 推进技术, 2013, 34(1): 69-75.

参考文献

[1] Curran Edward T.Scramjet Engines:The First Forty Years [J].Journal of Propulsion and Power, 1,7(6):1138-1148.
[2] Billig F S, Waltrup P J, Stockbridge R D.Integral-rocket Dual-Combustion Ramjets:a New Propulsion Concept [J].Journal of Spacecraft and Rockets, 1980,(5).
[3] Mercier Robert, McClinton C.Hypersonic Propulsion—Transforming the Future of Flight [R].AIAA 2003-2732.
[4] Kay I W,Peschke W T,Guile R N.Hydrocarbon-Fueled Scramjet Combustor Investigation [J].AIAA 90-2337.
[5] Situ M, Wang C, Lu H P, et al.Hot Gas Piloted Energy for Supersonic Combustion of Kerosene with Dual-Cavity [J].AIAA 2001-0523.
[6] Situ M, Wang C, Zhuang K G.Investigation of Supersonic Combustion of Kerosene Jets with Hot Gas Piloted Energy and Dual-Cavity [R].AIAA 2002-0804.
[7] 王春, 司徒明, 马继华,等.高温富油燃气超声速燃烧数值模拟[J].推进技术, 0,1(2):60-63.(WANG Chun, SITU Ming, MA Ji-hua, et al.Numerical Simulation on Supersonic Combustion of Fuel-Rich Hot Gas [J].Journal of Propulsion Technology, 0,1(2):60-63.)
[8] 于江飞, 晏至辉, 刘卫东.双燃烧室冲压发动机富油燃气超声速燃烧数值模拟[J].弹箭与制导学报, 9,9(2):169-173.
[9] 晏至辉, 陈逖, 于江飞,等.双燃冲压发烧室动机超声速混合层混合增强数值研究[J].航空动力学报, 0,5(4):821-828.
[10] 赵吕顺.碳氢燃料流向涡掺混超燃冲压发动机冷态数值研究[D].北京:北京航空航天大学, 2006.
[11] 介克, 杨占宇, 赵吕顺,等.马赫数2.5超/亚声流流向涡掺混超燃室冷态实验[J].航空动力学报, 7,2 (12).
[12] 赵吕顺, 单鹏, 介克,等.马赫数2.5超燃室中超/亚声流流向涡掺混冷态流场数值研究[J].空气动力学学报, 9,7(2).
[13] 黄勇, 林宇震, 樊未军,等.燃烧与燃烧室[M].北京:北京航空航天大学出版社,2009.
[14] Peng Shan, Zhan-yu Yang, Lu-shun Zhao, et al.Experimental Study on the Flame Holding Torch of a Hydrocarbon Fueled Combined Supersonic Combustor with a Pilot Burner and a Streamwise-Vortices Generator [R].AIAA 2011-6107.