某型航空发动机压气机叶片气动负荷的近似计算

以某型航空发动机压气机四、五、六级动叶为研究对象，在缺乏叶片扭向设计参数的情况下，根据发动机在地面标准大气条件、设计转速下计算所得的气流参数——压力、温度和速度，应用压气机增压过程中的能量转换关系及级压缩功的表达式，并考虑到动叶受力远大于静叶受力、动叶故障率远大于静叶故障率的事实，近似计算了发动机设计转速下四、五、六级动叶的气动负荷随叶高的变化，从而找到了一种叶片气动负荷的近似计算方法，并为叶片强度校核及振动分析打下了基础。

An Approximate Calculation of Aerodynamic Load for a Certain Type of Aero-engine Compressor Blade

The compressor blades from class 4 to class 6 in a certain type of engine are taken as the objects of study. Based on the standard ground atmosphere and the aerodynamic parameters such as the pressure, the temperature and the velocity calculated under the condition of the design rotating velocity and with the blade twist law being unknown, the aerodynamic loads borne by the rotating blades are calculated approximately. During the calculation, the energy conversion relations in the course of compressor pressurizing and the expression of stage compression work are used, the fact that the loads borne by the rotating blades are far greater than those borne by the static blades and simultaneously the fact that the breakdown rates of the rotating blades are much greater than those of the static blades are all taken into consideration. In this paper the changes of the aerodynamic loads of blades class 4 to class 6 with the blade height under the condition of the designed rotating speed of the engine are calculated approximately, thus an approximate calculating method for calculating blade aerodynamic load is found, which lays the foundation for the strength checking and the vibration analysis.