中文摘要：

为进一步缩减涡轮轴向尺寸,提升航空发动机推重比,在考虑冷气的影响下,将某型高负荷1＋1对转涡轮改型为1＋1/2对转涡轮,并对其内部流场加以分析。研究结果表明,与原型涡轮相比,改型设计在叶片数大幅减少的前提下,效率略有提高且保证了原有的做功量基本不变。此外,对于此类涡轮设计,需考虑大冷气量下通流设计及叶片匹配、高出口马赫数叶型尾缘激波控制、高来流马赫数叶型设计以及高负荷涡轮叶片通道中通道涡对冷却效果的影响等问题。

英文摘要：

In order to decrease the axial length and enhance the thrust-weight ratio of the aero engine,a 1＋1 counter-rotating turbine has been redesigned into a 1＋1/2 counter-rotating turbine by fully 3D design method with coolant flow taken into consideration,and the internal flow field has been analyzed.The result showed that newly designed 1＋1/2 counter-rotating turbine achieves the performance of the original turbine with an acceptable efficiency,and decreases the blade number and axial length of the turbine at the mean time.In addition,issues like through flow design and blades matching under high coolant flow rate condition,shock wave control of high exit Mach number,blade profile design of high inlet Mach number and influence on cooling effect by passage vortex in high-loaded turbine passages should be taken into consideration during designing process.