冷气掺混对高压涡轮气动性能影响的数值研究

采用数值方法研究了冷气掺混对高压涡轮气动性能和叶栅通道内部二次流动结构的影响，计算结果表明:冷气流量增加，冷却高压涡轮导叶和转子型面总载荷降低，导叶进、出口马赫数均减小，转子出口相对马赫数在径向0~0.55区域增大而在径向0.55~1.0区域减小.导叶进、出口气流角受冷气流量的变化影响较小.冷气流量由压气机进口流量的4.83%增加至14.49%，转子进口相对气流角在径向0.05~0.95区域增大而出口相对气流角在径向0.6~1.0区域减小，导叶绝热壁面冷却效率先升高后降低而转子绝热壁面冷却效率提高了19.33%.轮毂和机匣封严气呈束状进入转子叶栅通道且腔内封严气流动受旋转轮盘抽吸效应影响较大. 

Numerical study on influence of coolant injection on the aerodynamic performance of high pressure turbine

Influence of coolant injection on the aerodynamic performance of high pressure turbine and secondary flow structure in cascade channel were numerically simulated. The results indicate that cooling high-pressure turbine vane and rotor load decreased, vane inlet and outlet Mach number decreased, rotor outlet relative Mach number increased in the radial region from 0 to 0.55, but decreased in the radial region from 0.55 to 1.0 with the increase of cooling air mass flow. Vane inlet and outlet flow angle was less affected by cooling air mass flow change. Cooling air mass flow increased from 4.83% to 14.49% of compressor inlet mass flow, rotor inlet relative flow angle increased in the radial region from 0.05 to 0.95, but outlet relative flow angle decreased in the radial region from 0.6 to 1.0; adiabatic wall cooling efficiency of vane first increased and then decreased while adiabatic wall cooling efficiency of rotor gradually improved by 19.33%. Hub and case sealing gas entered into the rotor cascade channel in bundles, with cavity sealing gas flow was greater affected by the pump effect of rotating wall.