基于煤油燃料的斜爆轰发动机性能数值模拟  

Numerical simulation of oblique detonation engine performance based on kerosene fuel

作　　者：杜鹏 薛瑞 王晨[2] 张云天 徐朝启 DU Peng;XUE Rui;WANG Chen;ZHANG Yuntian;XU Chaoqi(State Key Laboratory for Strength and Vibration of Mechanical Structures,School of Aerospace Engineering,Xi’an Jiaotong University,Xi’an 710049,China;Key Laboratory of Intelligent Control and Optimization for Industrial Equipment,Ministry of Education,Dalian University of Technology,Dalian Liaoning 116024,China)

机构地区：[1]西安交通大学航天航空学院机械结构强度与振动国家重点实验室,西安710049 [2]大连理工大学工业装备智能控制与优化教育部重点实验室,辽宁大连116024

出　　处：《航空动力学报》2023年第10期2349-2359,共11页Journal of Aerospace Power

基　　金：国家自然科学基金(51706170);中国博士后科学基金(2019TQ0246,2019M663734);陕西省自然科学基础研究计划基金(2020JQ-007);中央高校基本科研业务费专项资金(xzy012019053,xjh012019033);陕西省自然科学基金面上项目(2022JM-231)。

摘　　要：针对马赫数为8以上高超声速飞行器的应用问题,采用11组分-10反应步的煤油/空气化学反应动力学模型,对不同来流及燃料喷注条件下的斜爆轰模型发动机进行数值研究,获得其对燃烧室内起爆驻定、爆轰波波面结构及推进性能的影响规律。研究结果表明:燃烧室入口马赫数为4.3时,超声速来流与壁面边界层作用加速了点火起爆过程,爆轰波在短时间内驻定。随着来流速度增大,爆轰波驻定位置更靠近燃烧室下游,爆轰波与边界层相互作用产生分离泡导致斜爆轰发动机推力显著降低。燃料当量比的变化直接影响爆轰波波面结构,减小当量比使得斜爆轰波稳定性降低,光滑的波面转变为“锯齿”状结构,具有该结构的爆轰波流场会显著降低发动机推进性能。According to the application problem of hypersonic vehicles above Mach number of 8,the 11 component/10-reaction steps kerosene chemical reaction kinetics model was adopted to perform numerical simulations about the two-dimensional model of oblique detonation engines under different inlet and fuel injection conditions.The effect of incoming Mach number on initiation and stabilization of detonation waves in the combustor,and the effect of fuel equivalent ratio on detonation wave surface structures,and the engine propulsion performance were obtained.The results showed that the effect of the supersonic flow and the wall boundary layer accelerated the detonation initiation process,and the detonation wave stabilization was completed shortly when the inlet Mach number of the combustor was 4.3.Continuing to increase the incoming Mach number made the stabilization position of the detonation wave closer to the downstream.The separation bubble generated by the interaction of the detonation wave and the boundary layer caused the thrust of the oblique detonation engine to be significantly reduced.The fuel equivalent ratio directly affected the detonation wave surface structure.Reducing the equivalence ratio reduced the stabilization of the oblique detonation wave,and the smooth wave surface was transformed into a sawtooth structure.The detonation wave flow field with this structure could significantly reduce its propulsion performance.

关 键 词：斜爆轰发动机 煤油 爆轰波 起爆 超声速燃烧 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]