冷却流量偏差对超燃冲压发动机飞行速域影响  

Effect of cooling flow deviation on flight velocity region of scramjet

作　　者：姜俞光 戚永健 段艳娟 鲍文[3] 范玮[1] JIANG Yuguang;QI Yongjian;DUAN Yanjuan;BAO Wen;FAN Wei(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;National Key Laboratory of Solid Rocket Propulsion,The Institute of Xi’an Aerospace Solid Propulsion Technology,Xi’an 710025,China;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]西安航天动力技术研究所固体推进全国重点实验室,西安710025 [3]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《航空动力学报》2025年第1期21-34,共14页Journal of Aerospace Power

基　　金：国家自然科学基金(51906207,U22B2091)。

摘　　要：针对碳氢燃料流量偏差问题对超燃冲压发动机马赫数许用上限影响的问题,建立准一维燃烧与冷却耦合模型,同时对其进行了验证,作为总体分析工具;仿真结果表明:超燃冲压发动机工作范围受流量偏差的影响,以流量偏差β=-0.5为例,流量偏差将使得发动机飞行马赫数上限从Ma=6降低至Ma=5,说明流量偏差将严重限制发动机的安全运行速域,影响飞行任务;通过对比分析不同燃烧与冷却设计,如逆流冷却、两点喷油、偏差起始位置、最大许用壁温/油温等,对飞行马赫数上限的影响机制,发现其可减弱流量偏差,拓宽发动机工作范围;最后基于分级节流流量偏差抑制方法的试验数据,分析了此方法拓宽发动机工作范围的能力,发动机工作速域上限整体拓宽接近1个马赫数范围。The influence of hydrocarbon fuel flow deviation on the allowable Mach number upper limit of scramjet was focused and researched.A quasi-one-dimensional coupling model of combustion and cooling was established and verified as an overall analysis tool.The simulation results showed that the working range of scramjet was seriously affected by the flow deviation.Taking the flow deviation=−0.5 as an example,the flow deviation lowered the upper limit of the engine flight Mach number from Ma=6 to Ma=5,indicating that the flow deviation seriously restrained the safe operating speed range of the engine and affected the flight mission.The influencing mechanism of different combustion and cooling designs on the upper Mach number limit was compared and analyzed,such as counter flow cooling,multi-stage fuel injection,flow deviation initial position,and maximum wall/fuel temperature.The flow deviation was suppressed and the flight Mach number range was broadened.Finally,based on the experimental data of the cascade-throttle flow deviation suppression method,the upper flight Mach number limit of the engine was extended by 1 Mach number.

关 键 词：碳氢燃料 再生冷却 流量偏差 飞行马赫数 发动机性能 超燃冲压发动机 

分 类 号：V233.5[航空宇航科学与技术—航空宇航推进理论与工程]