航空发动机

仝照旭，韩启祥.钝体火焰稳定器后燃烧不稳定数值模拟[J].航空发动机,2023,49(1):81-88

钝体火焰稳定器后燃烧不稳定数值模拟

Numerical Simulation of Combustion Instability Behind Bluff Body Flame Holder

DOI：

英文关键词:afterburner bluff body flame holder combustion instability numerical simulation aeroengine

基金项目:国家自然科学基金（51676097）资助

作者	单位	E-mail
仝照旭，韩启祥	南京航空航天大学能源与动力学院，南京210016	taa123@nuaa.edu.cn

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中文摘要:

为了缓解航空发动机加力燃烧室中频繁出现的燃烧不稳定现象，利用商业软件Fluent对带钝体火焰稳定器的模型加力燃烧室进行基于大涡模拟（LES）的3维热态数值仿真。通过分别改变加力燃烧室的来流温度、来流马赫数、燃油当量比3种影响燃烧的关键因素来分析其对火焰稳定器后燃烧不稳定现象的影响。结果表明：来流温度从600 K提升到1200 K时，钝体稳定器后火焰形式由直线状的剪切层火焰向波浪状的漩涡火焰转变，燃烧不稳定机制由K-H不稳定向BVK不稳定转变；来流马赫数从0.1 提高到0.3时，燃烧不稳定的脉动频率随之提高，压力脉动的幅值随之增大，但放热脉动的幅值先增大后减小；燃油当量比从0.5增大到0.7时，燃烧不稳定的频率变化较小，压力脉动与放热脉动的幅值存在先增后减的趋势。

英文摘要:

In order to alleviate the frequent combustion instability problems in aeroengine afterburners，the 3D thermal numerical sim? ulation based on large eddy simulation（LES）for a model afterburner with bluff body flame stabilizer was carried out by using commercial software Fluent. Three key factors about the temperature of the incoming gas，the Mach number of the incoming gas and the fuel equivalent ratio were analyzed for their influence on combustion instability after the flame holder. The results show that when the inlet temperature ris? es from 600 K to 1200 K，the flame form behind the flame stabilizer changes from straight shear layer flame to wavy vortex flame，and the combustion instability mechanism changes from K-H instability to BVK instability. When the incoming Mach number increases from 0.1 to 0.3，the frequency of combustion instability increases，and the amplitude of pressure pulsation also increases，but the amplitude of exother? mic pulsation increases first and then decreases. When the fuel equivalent ratio increases from 0.5 to 0.7，the frequency of combustion insta? bility changes slightly，and the amplitude of pressure pulsation and exothermic pulsation tends to increase first and then decrease.

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