斜爆震发动机进气道与燃烧室一体化设计仿真研究

推进技术 ›› 2018, Vol. 39 ›› Issue (9): 1938-1947.

斜爆震发动机进气道与燃烧室一体化设计仿真研究

陈嘉豪,张义宁,杨晖,宫继双,朱守梅

北京动力机械研究所激光推进及其应用国家重点实验室，北京 100074,北京动力机械研究所激光推进及其应用国家重点实验室，北京 100074,北京动力机械研究所激光推进及其应用国家重点实验室，北京 100074,北京动力机械研究所激光推进及其应用国家重点实验室，北京 100074,北京动力机械研究所激光推进及其应用国家重点实验室，北京 100074

发布日期:2021-08-15
作者简介:陈嘉豪，男，硕士生，研究领域为斜爆震发动机技术。E-mail: alanchen_jh@163.com 通讯作者:张义宁，男，博士，研究员，研究领域为燃烧及新概念推进技术。
基金资助:
国家自然科学基金(91641130)。

Numerical Simulation on Integrated Design Inlet and Combustion Chamber of Oblique Detonation Engine

State Key Laboratory of Laser Propulsion and Application，Beijing Power Machinery Institute ，Beijing 100074，China,State Key Laboratory of Laser Propulsion and Application，Beijing Power Machinery Institute ，Beijing 100074，China,State Key Laboratory of Laser Propulsion and Application，Beijing Power Machinery Institute ，Beijing 100074，China,State Key Laboratory of Laser Propulsion and Application，Beijing Power Machinery Institute ，Beijing 100074，China and State Key Laboratory of Laser Propulsion and Application，Beijing Power Machinery Institute ，Beijing 100074，China

Published:2021-08-15

摘要/Abstract

摘要： 针对Ma10量级高超声速飞行器应用背景，为了实现斜爆震发动机一体化，基于氢气与空气预混来流条件，开展斜爆震发动机设计研究。通过压缩波系配置，分析进气道压缩过程对斜爆震发动机燃烧室入口参数影响规律；针对不同燃烧室入口条件，开展斜爆震驻定燃烧过程仿真分析，获得入口来流参数与几何参数对斜爆震燃烧组织过程影响规律；基于优选方案，开展斜爆震发动机进气道与燃烧室一体化数值仿真。研究结果表明:随着当量比、斜劈角增大，爆震波后的压力与温度与相应的爆震波角会增大；通过合理选取进气道与燃烧室结构参数，可以实现斜爆震发动机进气道压缩过程与燃烧组织过程的匹配。

关键词: 斜爆震；高超声速；驻定燃烧；一体化；数值仿真

Abstract: Aiming at the application background of the Ma10 hypersonic aircraft， in order to realize the integration of oblique detonation engine， based on hydrogen and air premixed flow conditions， a research on designing of oblique detonation engine was carried out. Firstly， the influence rules of inlet parameters of the combustion chamber of oblique detonation engine were analyzed by means of compression wave system configuration. Secondly， based on the inlet conditions of different combustion chamber， the simulation analysis of the stationary combustion process was carried out， and the influence rules of the flow parameters and geometric parameters on the process of the combustion organization of oblique detonation were obtained. Finally， based on the optimization scheme， the integrated numerical simulation of the inlet and combustion chamber of the oblique detonation engine was carried out. The results show that the pressure and temperature behind the detonation wave and the corresponding detonation wave angle will increase with the increase of the equivalent ratio and the angle of wedge. Through reasonable selection of the inlet and combustion chamber structure parameters， the compression process of the inlet of the oblique detonation engine can be matched with the combustion tissue process.

Key words: Oblique detonation；Hypersonic velocity；Stationary combustion；Integration；Numerical simulation

陈嘉豪,张义宁,杨晖,宫继双,朱守梅. 斜爆震发动机进气道与燃烧室一体化设计仿真研究[J]. 推进技术, 2018, 39(9): 1938-1947.

CHEN Jia-hao,ZHANG Yi-ning,YANG Hui,GONG Ji-shuang ,ZHU Shou-mei. Numerical Simulation on Integrated Design Inlet and Combustion Chamber of Oblique Detonation Engine[J]. Journal of Propulsion Technology, 2018, 39(9): 1938-1947.

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