涡轮级间燃烧室燃烧性能试验

丁国玉; 何小民; 金义; 秦伟林; 吴泽俊; 蒋波

涡轮级间燃烧室燃烧性能试验

南京航空航天大学能源与动力学院, 南京 210016

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出版历程
- 收稿日期: 2011-11-14
- 刊出日期: 2012-11-28

Experiment of performance of interstage turbine combustor

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 开展了进口空气马赫数、驻涡区余气系数影响涡轮级间燃烧室燃烧性能的试验研究,获得了燃烧室性能参数的变化规律:随着进口马赫数的增大,总压损失从1.5%增加到7%,流阻系数变化不大,出口温度分布系数OTDF(overall temperature distribution factor)也相应变大;对于不同的进口马赫数,燃烧效率、OTDF随驻涡区余气系数的增大分别为降低和基本不变;燃烧效率大多在70%~85%之间;试验中得到的在燃烧室进口温度为473K时的最大贫油熄火余气系数为9.7.
- 涡轮级间燃烧室 /
- 驻涡 /
- 燃烧性能 /
- 马赫数 /
- 余气系数
Abstract: Experiments were conducted to study the interstage turbine combustor performance with different inlet air Mach number and the excess air coefficient of cavity.Experimental result shows that total pressure loss increases from 1.5% to 7% varying with the increase of the inlet air Mach number,the flow drag coefficient is 16 which changes little with the inlet air flow Mach number,and overall temperature distribution factor (OTDF) increases with the increase of the inlet air Mach number;OTDF holds the line as the excess air coefficient of cavity increases while the combustion efficiency decreases;the combustion efficiency is almost between 70% through 85%;the maximal lean blow out(LBO) excess air coefficient is 9.7 at the inlet air temperature of 473K.
- interstage turbine combustor /
- trapped-vortex /
- combustion performance /
- Mach number /
- excess air coefficient

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参考文献(17)

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