双环预混旋流燃烧室点熄火性能试验研究

Test Study of the Ignition and Blow-out Performance of a TAPS Combustor

为了通过试验方法获得贫油点熄火边界,以双环预混旋流低污染燃烧室为研究对象,分析主燃级径向旋流器的叶片角度、旋转方向及多斜孔壁火焰筒的冷却孔偏转角等参数对燃烧室点熄火性能的影响。结果表明:主燃级旋流器叶片角度对燃烧室的点火性能影响不大;火焰筒冷却孔有偏转角且方向与主燃级旋流器旋向相同时的点火性能优于旋向相反时的点火性能;预燃级旋流器与主燃级旋流器旋向相反时,火焰筒冷却孔有偏转角且方向与主燃级旋流器旋向相同时的点火性能优于无偏转角时的点火性能,旋向相同时,则无明显影响;火焰筒冷却孔无偏转角时,预燃级旋流器与主燃级旋流器旋向相反的贫油熄火性能优于旋向相同时的贫油熄火性能。

In order to obtain the ignition and blow-out boundary of lean burn by test method,the influence of vane angle,swirling direction of the main stage swirler and deflection angle of cooling hole of inclined multi-hole liner on the ignition and blow-out performance of the combustor was analyzed by taking the twins annual premixed swirler low-emission combustor as the research object.The results show that the vane angle of main stage swirler has little effect on the ignition performance of combustor.When the swirling direction of liner cooling hole deflected angle is same with the main stage swirler,the ignition performance is better than that swirling direction is opposite.When swirling direction of pilot stage swirleris opposite to the main stage swirler and the swirling direction of liner cooling hole with deflected angle is same with the main stage swirler,the ignition performance is better than that deflected angle is zero.When swirling direction of pilot stage swirleris same as the main stage swirler,there is no difference on ignition performance.When the deflected angle of liner cooling hole is zero and swirling direction of pilot stage swirleris opposite to the main stage swirler,the blow-out performance is better than that swirling direction is same.