凹腔驻涡与径向组合稳定器的流动与燃烧特性  

Flow and combustion characteristics of trapped vortex cavity combined with radial flameholder

作　　者：康玉东 钟世林 彭维康 翟云超 邓远灏 KANG Yudong;ZHONG Shilin;PENG Weikang;ZHAI Yunchao;DENG Yuanhao(Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Chengdu 610500,China;Institute for 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1期13-20,共8页Journal of Aerospace Power

摘　　要：为了提升凹腔驻涡加力燃烧室的综合燃烧性能,获取径向稳定器倾角对组合稳定器系统流动及燃烧特性的影响规律,设计了安装倾角为5°、8°、10°、15°的凹腔驻涡加力燃烧室,采用数值模拟与试验验证相结合的方法,进行了不同余气系数下的综合燃烧性能研究。研究工况外涵温度为600 K、内涵温度为1000 K、内涵压力为180 kPa、涵道比为0.17、余气系数为1.27~2。获得了加力燃烧室流场、出口燃气温度、总压恢复系数、凹腔壁温、径向稳定器壁温变化规律。结果表明:与径向稳定器10°倾角相比,5°倾角下总压恢复系数低0.002~0.006、出口燃气温度高20~40 K、凹腔驻涡稳定器最高壁温低63~82 K、径向稳定器壁温高60~70 K。In order to improve the comprehensive combustion performance of trapped vortex cavity afterburner and better understand the effect of radial flameholder installation angle on flow and combustion characteristics,numerical and experimental investigation were employed at 5°,8°,10°,15°under different excess air coefficients.The investigations were performed under the bypass temperature 600 K,the core temperature 1000 K,the core pressure 180 kPa,the bypass ration 0.17,and excess air coefficient 1.27—2.Through investigation,the flow filed,exit temperature,total pressure recovery coefficient,wall temperature of trapped vortex cavity(TVC)and radial flameholder were obtained.The results showed that when the angle was 5°,the total pressure recovery coefficient was 0.002—0.006 lower,the exit temperature was 20—40 K higher,the TVC wall temperature was 63—82 K lower,the radial flameholder wall temperature was 60—70 K higher than that at the angle of 10°.

关 键 词：径向稳定器倾角 凹腔驻涡稳定器 加力燃烧室 流动特性 燃烧特性 

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]