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针对某1+1/2对转涡轮进行了气动设计及流场分析。在设计中,以降低高压转子通道中激波损失为目标,低压级载荷系数选择了较高和较低两种方案。分析表明,虽然第二种方案可以降低高压转子出口马赫数,但该方案亦具有过渡段损失较大等劣势,故本文最终选择了第一个方案。利用该方案,本文完成了1+1/2对转涡轮的气动设计并对该涡轮进行了三维数值分析。分析结果表明,所设计的1+1/2对转涡轮的流量和膨胀比皆满足总体需求,而效率尤其是低压级效率明显高于设计要求。与1+1对转涡轮相比,1+1/2对转涡轮高压静子和高压转子的叶片数明显减少。
The aerodynamic design and flow field analysis of a 1 + 1/2 counter - rotating turbine were carried out. In the design, the goal of reducing the shock wave in the high-pressure rotor passage is to choose the higher and lower load-shedding factors. The analysis shows that although the second scheme can reduce the Mach number of high-pressure rotor exit, this scheme also has the disadvantage of large loss in the transition section. Therefore, the first option is finally selected in this paper. With this scheme, the aerodynamic design of the 1 + 1/2 counter-rotating turbomachine is completed and the 3-D numerical analysis of the turbomachine is completed. The analysis results show that the designed 1 + 1/2 counter-rotating turbine flow and expansion ratio meet the overall demand, while the efficiency, especially the low-pressure stage efficiency is significantly higher than the design requirements. Compared with the 1 + 1 counter-rotating turbine, 1 + 1/2 counter-rotating turbine high-pressure stator and high-pressure rotor blade number decreased significantly.