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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。
In order to further reduce the axial size of turbines and enhance the thrust-weight ratio of aeroengines, a type of high-load 1 + 1 counter-rotating turbine was retrofitted into a 1 + 1/2 counter-rotating turbine under the influence of cold air and its internal flow field To analyze. The results show that, compared with the prototype turbine, the modified design slightly increases the number of blades, the efficiency is slightly increased and the original work done to ensure that the amount of power is basically unchanged. In addition, for such turbine design, it is necessary to consider the design of through-flow under large cooling capacity and blade matching, the high Mach-number trailing edge shock control at exit Mach number, the high flow Mach number leaf design and the passage vortex in high load turbine blade passage On the cooling effect and other issues.