1+1/2级超跨声对转涡轮气动性能试验及分析

对转涡轮是高性能航空发动机的关键技术之一。采用试验方法对某1+1/2级超跨声对转涡轮气动性能进行了研究与分析。针对试验中涡轮级间难以布置测点的问题，提出了基于特性反推的分步试验方法，然后对超跨声对转涡轮运行特性进行了详细分析。研究结果表明，该超跨声高压涡轮流量特性几乎不随膨胀比变化，而效率特性变化较大；高、低压涡轮喉道面积比在涡轮膨胀比分配中起到重要作用，该值低于设计状态时，总膨胀比满足设计要求下，高压涡轮膨胀比增大，低压涡轮膨胀比减小；高压涡轮出口气流角对低压涡轮运行特性影响显著。

Test and analysis on aerodynamic performance of 1+1/2 super-transonic counter-rotating turbine

The counter-rotating turbine is one of the key technologies of high performance aero-engines. Tests are conducted to analyze the aerodynamic performance of the 1+1/2 super-transonic counter-rotating turbine. To solve the problem that test points are difficult to be arranged between two stages, a stepwise test method based on the performance inverse calculation is put forward to analyze the running characteristics of the super-transonic counter-rotating turbine. The test results indicate that the characteristic of the mass flow of the super-transonic high pressure turbine remains almost unchanged with the change of the expansion ratio, while the efficiency characteristic of the turbine changes greatly. The throat area ratio of the high and low pressure turbines plays an important role in distribution of the expansion ratio of the turbine:when the ratio is lower than the design state, the expansion ratio of the high pressure turbine increases and the expansion ratio of the low pressure turbine decreases, with the total expansion ratio meeting the design requirement; the outlet flow angle of the high pressure turbine has a significant influence on the performance of the low pressure turbine.