低压涡轮低雷诺数条件下气动性能分析  

Aerodynamic Performance Analysis of Low Pressure Turbine at Low Reynolds Numbers

作　　者：王松涛[1] 刘勋[1] 周逊[1] 冯国泰[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学发动机气体动力研究中心,哈尔滨150001

出　　处：《汽轮机技术》2011年第5期324-327,共4页Turbine Technology

基　　金：APTD(航空推进技术验证计划)某咨询项目

摘　　要：对某型航空发动机低压涡轮末级进行了数值计算,对比分析了不同雷诺数条件下该级涡轮的气动性能。通过计算分析低雷诺数条件对压力场和损失系数的影响,可以看出,与高雷诺数条件相比,在低雷诺数条件下,低压涡轮效率明显降低,损失增大,扩压段增加,横向压力梯度增加,附面层增厚。雷诺数的降低,导致黏性力增加,在静叶片吸力面出现分离区,而且随着雷诺数的降低,分离区加大。This paper calculated the last stage of a low pressure turbine and compared and analyzed the aerodynamic performance at different Reynolds Numbers. By calculating and analyzing the impact of low Reynolds numbers for pressure field and loss coefficients, compared with that at high Reynolds numbers, we can see that at low Reynolds numbers, efficiency of low pressure turbine decreases significantly; losses increases; diffuser section increases; transverse-pressure gradient increases; boundary layer incrassates. As the reduction of Reynolds number, viscous force increases, with the emergence of separation region at the suction side of the stator, and the separation region expands with the Reynolds number decreasing.

关 键 词：低雷诺数 涡轮 数值模拟 气动性能 

分 类 号：TK471[动力工程及工程热物理—动力机械及工程]