重型燃气轮机透平气动性能研究

Turbine Aerodynamic Performance Research of Heavy-duty Gas Turbine

为提高某重型燃气轮机单轴多级透平气动性能,利用航空发动机设计及校核程序,对某重型燃气轮机透平的设计进行了反演算,利用1维平均半径流场的计算方法进行了计算分析,得出了气动参数的展向分布,并进行了透平冷、热态流道的计算对比,分析了大尺寸透平尺寸换算的变化规律,通过采用变比热、多损失模拟的准3维正问题计算方法,对结果进行了校核计算。结果表明:采用现有的航空发动机设计平台进行重型燃机单转子多级透平反问题设计和正问题校核计算误差较小,其技术可靠,为进一步利用该体系完成透平性能改进打下了基础。

The design of a heavy-duty gas turbine was inversely ealculated to improve the aerodynamic performanee the single shaft muhi-stage turbine by the design and check program of aeroengine. The turbine design was calculated and analyzed by the calculation method of one-dimensional average radius flow field. Spanwise distribution of the aerodynamic parameters was deduced. The cool and hot passage of the turbine were calculated and compared, and the change rules of large scale turbines dimension-scaling were analyzed. The results were ehecked by the calculation method of the varying speeific heat and multi-loss simulation quasi three-dimensional direct problem. The results indicate that there is a relatively small calculating error between design in indirect problem and check in direct problem of the single shaft muhi-stage turbine using current aeroengine design platform. The technique is reliable. The results are the basis of improving turbine performance.