斜爆震发动机进气道与燃烧室一体化设计仿真研究

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

关键词:  斜爆震  高超声速  驻定燃烧  一体化  数值仿真

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

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。

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.