燃气轮机压气机动叶片设计与计算  

Rotor Blade Design and Calculation of Gas Turbine Compressor

作　　者：肖贾光毅 忻建华[1] 

机构地区：[1]上海交通大学机械与动力工程学院,上海200240

出　　处：《热力透平》2016年第1期24-28,共5页Thermal Turbine

摘　　要：利用传统压气机叶片亚音速设计方法,针对某重型燃气轮机压气机某级动叶片,采用等环量与等进口气流角沿径向气流参数分布规律的方法设计了两种叶片。利用数值模拟的方法对两种叶片在额定工况与变攻角工况下的气动性能进行分析,探究了传统叶片设计方法在重型燃轮机设计中的可行性与适用范围。计算结果表明,本设计在压气机叶片中径处来流气体相对马赫数低于0.6的情况下是比较成功的,该方法可以应用于重型燃气轮机压气机和低亚声速级的叶片设计中。Aimed at a rotor blade of a heavy-duty gas turbine, two blades with free vortex and constant α1 root-to-top gas parameter regulations were designed separately using traditional subsonic compressor blade design method. The blades＇ aerodynamic performances under designed and variable incidence working conditions were analyzed with the help of numerical method, and the feasibility and the scope of this traditional blade design method in heavy-duty gas turbine blade designs were studied. The calculation results indicate that the blade design is successful in the condition where the mid-span inlet air Mach number of compressor blades is lower than 0. 6. This method can be used in design of heavy-duty gas turbine compressor blades under the subsonic conditions.

关 键 词：叶片设计 数值模拟 等环量叶型 等进口气流角叶型 

分 类 号：TK474.8[动力工程及工程热物理—动力机械及工程]