基于亚燃的高超声速冲压发动机内流道研究

doi:10.7527/S1000-6893.2014.0236

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基于亚燃的高超声速冲压发动机内流道研究

段晰怀¹, 郑日恒^1,2, 李立翰^1,2

1. 北京动力机械研究所, 北京 100074;
2. 北京动力机械研究所高超声速冲压发动机技术重点实验室, 北京 100074

收稿日期:2014-08-24 修回日期:2014-10-20 出版日期:2015-01-15 发布日期:2014-10-21
通讯作者: 郑日恒,Tel.: 010-68375352 E-mail: riheng@hotmail.com E-mail:riheng@hotmail.com
作者简介:段晰怀男,硕士。主要研究方向:航空宇航推进理论与工程冲压发动机总体技术。 E-mail: duanxihuai@163.com;郑日恒男,博士,教授。主要研究方向:超声速/高超声速冲压发动机,高超声速组合循环发动机,进气道与尾喷管中的复杂动力学。 Tel: 010-68375352 E-mail: riheng@hotmail.com
基金资助:
高超声速冲压发动机技术重点实验室开放基金(20120103006)

Internal flowpath for hypersonic ramjet based on subsonic combustion

DUAN Xihuai¹, ZHENG Riheng^1,2, LI Lihan^1,2

1. Beijing Power Machinery Institute, Beijing 100074, China;
2. Science and Technology on Scramjet Laboratory, Beijing Power Machinery Institute, Beijing 100074, China

Received:2014-08-24 Revised:2014-10-20 Online:2015-01-15 Published:2014-10-21
Supported by:
Science and Technology on Scramjet Laboratory Open Fund (20120103006)

摘要/Abstract

摘要：

为了研究亚燃冲压发动机在高超声速条件下工作的性能,采用总体性能计算方法和流体力学仿真对基于突扩燃烧的高马赫数亚燃冲压发动机内流通道进行匹配设计研究,得到了其速度特性和调节特性。结果表明,设计出的亚燃冲压发动机在高超声速范围内性能良好,能够正常工作。在接力点处, 马赫数Ma=3.5,高度H=12 km,得到最大推力系数为0.649,此时比冲为13 801.2 N·s/kg;在巡航点处,Ma=5.0,H=21 km,发动机余气系数α=1.8时,得到推力系数为0.370,此时最大比冲为12 574.0 N·s/kg。研究认为,最大飞行马赫数为5~6的高超声速冲压发动机采用亚燃是可行的。

关键词: 高超声速, 亚燃冲压发动机, 内流道, 可行性, 仿真计算

Abstract:

To explore the performance of subsonic combustion ramjet working at hypersonic incoming flow conditions, the matching of internal flowpath of a ramjet based on dump combustion chamber is studied. The performance of the engine is obtained by means of integrated performance computation and fluid dynamics simulation. The results indicate that the designed subsonic combustion ramjet has good performance at hypersonic incoming flow conditions and works well. At the booster-to-ramjet transition point with Mach number Ma=3.5, altitude H=12 km, the thrust coefficient has its maximum value of 0.649 and the specific impulse is 13 801.2 N·s/kg. At the cruising condition with Mach number Ma=5.0, altitude H=21 km, excess air coefficient α=1.8, its specific impulse has its maximum value of 12 574.0 N·s/kg, and the thrust coefficient is 0.370. This study shows that the hypersonic ramjet with subsonic combustion for the maximum incoming Mach number between 5 and 6 is feasible.

Key words: hypersonic, subsonic combustion ramjet, internal flowpath, feasibility, simulating calculation

中图分类号:

V430

段晰怀, 郑日恒, 李立翰. 基于亚燃的高超声速冲压发动机内流道研究[J]. 航空学报, 2015, 36(1): 232-244.

DUAN Xihuai, ZHENG Riheng, LI Lihan. Internal flowpath for hypersonic ramjet based on subsonic combustion[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(1): 232-244.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于亚燃的高超声速冲压发动机内流道研究

Internal flowpath for hypersonic ramjet based on subsonic combustion

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