凹腔驻涡加力燃烧室联焰特性研究  

Cross-flame characteristic of the trapped vortex afterburner

作　　者：邱皓 邓远灏 王金涛 翟云超 QIU Hao;DENG Yuanhao;WANG Jintao;ZHAI Yunchao(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2023年第6期21-28,共8页Gas Turbine Experiment and Research

摘　　要：为了研究凹腔驻涡加力燃烧室的联焰特性,设计了一种凹腔驻涡加力燃烧室试验件,并采用试验和数值仿真的方法对其联焰特性进行了研究。试验采用航空煤油作为燃料,燃油喷嘴采用离心式喷嘴。试验中,外内涵进气压比在0.97~1.07之间变化,稳定器前马赫数在0.17~0.25之间变化。研究结果表明,稳定器前马赫数在0.17~0.23之间时凹腔的联焰性能变化不明显,稳定器前马赫数超过此范围后凹腔的联焰性能变差;外内涵进气压比超过1.04后,凹腔壁温能达到的最大值降低,凹腔的联焰性能变差。In order to study the cross-flame characteristics of the trapped vortex afterburner,a trapped vortex afterburner was designed,and its cross-flame characteristics were studied by experimental research and numerical simulation.During the experiment,aviation kerosene and centrifugal nozzle were used.The external inlet pressure ratio varied between 0.97 and 1.07,and the Mach number in front of the stabilizer varied between 0.17 and 0.25.The results show that when the Mach number in front of the stabilizer varies between 0.17 and 0.23,and the change of the cavity’s cross-flame performance is not obvious.When the Mach number exceeds this range,the cavity’s cross-flame performance becomes worse.When the external internal pressure radio exceeds 1.04,the maximum value of the cavity wall temperature decreases,and the cavity’s cross-flame performance becomes worse.

关 键 词：航空发动机 凹腔驻涡 离心式喷嘴 加力燃烧室 联焰特性 数值仿真 试验研究 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]