凹腔参数对加力燃烧室贫油点火性能影响研究  

Lean ignition performance of trapped vortex cavity afterburner with different cavities

作　　者：王金涛 钟世林 康玉东 邓远灏 张飞 WANG Jintao;ZHONG Shilin;KANG Yudong;DENG Yuanhao;ZHANG Fei(Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Chengdu 610500,China;Institute of Aero Engine,Tsinghua University,Beijing 100084,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500 [2]清华大学航空发动机研究院,北京100084

出　　处：《航空动力学报》2025年第2期363-370,共8页Journal of Aerospace Power

摘　　要：为了研究凹腔结构参数对驻涡加力燃烧室贫油点火性能影响规律,设计了3种凹腔进气缝宽度、两种凹腔外廓结构的试验件。采用试验研究方法,对不同试验件方案、不同气流参数下驻涡加力燃烧室点火性能进行研究。试验马赫数为0.17~0.3、压比为0.97~1.08。获得了驻涡加力燃烧室点火马赫数边界、点火油气比变化规律和预测方法。结果表明:随着马赫数和压比增加,贫油点火油气比增加;较大外廓结构、较小进气缝宽度的凹腔稳定器点火性能更加优异;计算模型可有效预测贫油点火油气比,预测精度在20%以内。Three different kinds of mixed air gaps and two different kinds of cavity structures were designed to study the lean ignition performance of trapped vortex cavity afterburner.The experimental researches with different cavities and flow parameters were carried out.The investigation was performed with the mainstream Mach number ranging from 0.17 to 0.3,the pressure ratio of secondary flow to mainstream flow ranging from 0.97 to 1.08.The ignition Mach number,fuel air ratio and predictive model of the trapped vortex cavity afterburner were obtained.The results showed that the fuel air ratio increased with the increasing mainstream Mach number and the pressure ratio of secondary flow to mainstream flow.The bigger cavity with smaller mixed air gap was better for ignition.A predictive model was developed for the fuel air ratio.The error between the predicted value and the experimental value was not greater than 20%.

关 键 词：驻涡加力燃烧室 贫油点火 凹腔结构 气流参数 预测模型 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]