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涡轮导向器尾缘的精细结构由于加工误差的存在,会导致流道流通面积的改变,进而会使涡轮性能发生改变。从实际工程问题出发,采用数值模拟的方法,研究了某型发动机低压涡轮导向器尾缘的“劈缝”冷却结构由于变形导致的尾缘前后(叶盆尾缘处流道面积T1和叶背尾缘处流道面积T2)面积变化对涡轮流场和性能的影响。研究结果表明:在设计状态下,涡轮的喉道为T2;当T2大于设计值时,涡轮功率和涡轮流量变大,涡轮效率和涡轮功变小,但是涡轮的功率存在一个最高值的T2;当T1大于设计值时,涡轮效率和涡轮功增加。
The fine structure of the turbine guide trailing edge due to the existence of machining errors, will lead to changes in the flow area of the runner, which will make the turbine performance changes. Based on the actual engineering problems, numerical simulation is used to study the influence of deformation on the leading edge of the trailing edge of the low-pressure turbine guide Effect of area change of flow path area T2 at the trailing edge of blade on turbine flow field and performance. The results show that the throat of the turbine is T2 under the condition of design. When T2 is greater than the designed value, the turbine power and turbine flow rate become larger, the turbine efficiency and turbine work become smaller, but the turbine power has a highest value of T2. When T1 is greater than the design value, turbine efficiency and turbine work increase.