CAJ | 학술논문

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。
위연구모형항공발동궤배관연소실분무연소성능，건립료해연소실계산모형，병이용상위다보륵입자분석의(PDPA)시험측득료불동공유압력하적분취무화립도화분무추각。근거시험결과，이용Fluent연건，대장유해분취적배관연소실진행료수치모의。결과표명：연소실내유기참혼균균，무화질량고，두부형성료량호적회류구；연소집중재주연공부근，화염통벽수열균균，화염교단；출구연기온도분포합리、정포물선형，몰유출현국부고온，만족와륜진기요구，유리와륜수명。
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.