高频燃烧不稳定性单喷注器燃烧室模拟实验的研究  

Simulation test of high-frequency combustion instabilities of chamber with single injector

作　　者：张蒙正[1] 张志涛[2] 李鳌[2] 汪亮[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]西安航天动力研究所,陕西西安710100

出　　处：《实验技术与管理》2008年第3期28-32,共5页Experimental Technology and Management

摘　　要：高频燃烧不稳定性单喷注器燃烧室常压燃烧的模拟实验依据相似理论在大气环境下进行。模拟燃烧室采用与实际燃烧室有相同声学频率的模拟件，喷注器采用实际尺寸喷注器，实验介质为高温富氧空气和蒸气煤油。Ⅱ2=（P。/PF）^0.5（QVo／qvf）作为确定性相似准则，Ⅱ1=v/（Lf）为被确定性相似准则。改变富氧空气流量，调节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。用同轴湍流射流混合流场的经验公式估算燃烧区的特征长度，通过相似准则和燃烧室热力学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煤油、空气和氧气供应系统，流量控制和测量系统，空气甲烷燃烧器，富氧空气和煤油换热器，模拟燃烧室和喷注器，实验参数采集和处理系统，冷却水供应及控制系统等。发动机实验表明，模拟实验系统和方法是可行的。The simulation test of high- frequency combustion instabilities with single injector chamber is conducted in the atmospheric circumstance according to the similar theory. The simulation chamber is a reduced scale element which has the same natural frequency as the actual chamber＇s. The injector is actual one. The kerosene smoke and high temperature full-oxygen air are used to test medium. Ⅱ2 = （Po/Pf）^0.5（Qvo/qVf） is used as the similitude rule that was certain. Ⅱl = v/ （Lf） is used as the similitude rule that needs to be ascertained. The phase＇s connection between the acoustic oscillation and chamber pressure oscillation was changed by changing the full- oxygen air mass flow rate. The characteristic length of chamber combustion area was calculated from the experiential formula of coaxial turbulence mixing length. The simulation test parameters can be translated to actual engine work parameters by the si- militude rule and thermodynamic parameters. The simulation test system includes kerosene, air and oxygen supply system, air and methane combustion chamber, full-oxygen air and kerosene heat exchanger, simulation chamber, experimental injector, experimental data record and control system and other supply system. The engine test results during large- range change in work parameters prove the validity of atmospheric pressure combustion simulation test.

关 键 词：高频燃烧不稳定性 单喷注器 燃烧室 模拟实验 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程]