高频燃烧不稳定性全尺寸头部燃烧室低压燃烧模拟实验的原理及实现  

Principle and realization of high-frequency combustion instabilities simulation test of full size chamber

作　　者：张蒙正[1] 

机构地区：[1]西安航天动力研究所

出　　处：《实验技术与管理》2008年第10期38-41,共4页Experimental Technology and Management

摘　　要：高频燃烧不稳定性一直是液体火箭发动机研制中最困难问题之一,模拟实验是有理论和实际意义的研究方法。全尺寸头部燃烧室低压燃烧模拟实验采用实际燃烧室的头部和身部,用高温空气和气态燃料作介质,在较低的燃烧室压力下进行模拟实验。依据相似理论,选择被确定性相似准则和确定性相似准则,通过改变空气流量、温度、气态燃料的流量以及燃烧室喉部调节锥位置而改变燃烧室声学振荡和燃烧脉动的相位关系,激励起燃烧室高频不稳定性燃烧。通过相似准则和燃烧室热力参数将实验结果换算到实际发动机工况。整套模拟实验系统包括空气加热器、换热器、燃料蒸发器、模拟燃烧室、空气和燃料供应及控制系统、实验参数采集和处理系统、冷却水供应及控制系统等。系统可用于研究特定燃烧室的高频燃烧不稳定性裕度、抗脉动装置的效果、不同喷注器排列方案的相对优劣以及发动机启动阶段的工作特性。The combustion instability has long been recognized as one of the most difficult problems in the development of liquid propellant rocket engines. The simulation test research of high- frequency instability is of great significance in theory and practice. The simulation test of high frequancy compustion instabilities with full size chamber is conducted with lower chamber pressure. According to the similar theory, the simulation chamber is a real one which has the full size as the actual chamber. The fuel smoke and high temperature air were used to test medium. The similitude nile that needs to be ascertained is used and the similitude rule that was certained is also used. The phase＇s connection between the acoustic oscillation and chamber pressure oscillation was changed by changing the air mass flow rate, temperature, fuel mass flow rate and location of chamber laryngeal conditioner. The simulation test parameters can be translated to actual engine work parameters by the similitude rule and thermodynamic parameters. The simulation test system includes air heater and heat exchanger, fuel evaporator, simulation chamber, fuel and air supply and control system, experimental data record and control system and cooling water supply and control system. The simulation test system can obtain the high- frequency instability borderline of designed chamber. It can be used to investigate the effect of aseismatic device, the characteristic of design project with different injector arranged and start- up characteristic of engine.

关 键 词：高频燃烧不稳定性 全尺寸头部燃烧室 模拟实验 实验原理 实验系统 

分 类 号：V434.13[航空宇航科学与技术—航空宇航推进理论与工程]