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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.
The experimental study on the combustion performance of turbine inter-stage combustor was carried out with the inlet air Mach number and residual vortex coefficient in the vortex area. The variation law of the combustion chamber performance parameters was obtained. With the increase of the inlet Mach number, the total pressure loss decreased from 1.5% To 7%, the flow resistance coefficient does not change much and the OTDF (overall temperature distribution factor) also increases correspondingly. For different inlet Mach number, the combustion efficiency and OTDF increase with the residual vortex coefficient The combustion efficiency is mostly between 70% ~ 85%; the maximum residual lean burn air coefficient obtained in the experiment when the inlet temperature of the combustion chamber is 473K is 9.7.