航空发动机环管燃烧室喷雾燃烧性能研究  

Spray Combustion Performance of an Aero-Engine Cannular Combustor

作　　者：王成军[1] 江平[1] 曾文[1] 刘凯[1] 马洪安[1] 

机构地区：[1]沈阳航空航天大学航空航天工程学部,辽宁沈阳110136

出　　处：《燃气涡轮试验与研究》2014年第1期32-35,5,共5页Gas Turbine Experiment and Research

摘　　要：为研究某型航空发动机环管燃烧室喷雾燃烧性能,建立了该燃烧室计算模型,并利用相位多普勒粒子分析仪(PDPA)试验测得了不同供油压力下的喷嘴雾化粒度和喷雾锥角。根据试验结果,利用Fluent软件,对装有该喷嘴的环管燃烧室进行了数值模拟。结果表明:燃烧室内油气掺混均匀,雾化质量高,头部形成了良好的回流区;燃烧集中在主燃孔附近,火焰筒壁受热均匀,火焰较短;出口燃气温度分布合理、呈抛物线形,没有出现局部高温,满足涡轮进气要求,有利涡轮寿命。To investigate spray combustion performance in a certain type of aero-engine cannular combus-tor, a combustor calculation model was established. By using Phase Doppler Particle Analyzer （PDPA）, at-omizing particle size and spray angle were obtained under different oil pressure conditions. According to the test results, numerical simulation of the cannular combustor was conducted by the Fluent software. The test results show that atomization effect is good because the fuel and gas mixes uniformly with a good return ar-ea. Combustion flame is short near the main combustion hole. There is no local high temperature, the hot zone distribution of exit gas is reasonable, and meets the turbine inlet requirements, which is favorable for turbine life.

关 键 词：航空发动机 环管燃烧室 喷嘴雾化 出口燃气温度 多普勒粒子分析仪 数值模拟 

分 类 号：V231.23[航空宇航科学与技术—航空宇航推进理论与工程]