转子叶片加工误差对1.5级跨声速压气机气动性能的影响

压气机叶片加工误差不可避免，将在一定程度上影响压气机的气动性能。为研究叶片加工误差对跨声速压气机气动性能的影响，以燃气轮机进口1.5级跨声速压气机为对象，通过三坐标测量跨声速转子叶片叶型数据，获得了加工误差分布特征；针对实测转子叶片，采用三维CFD数值模拟方法，研究了轮廓度、位置度和扭转角综合误差对压气机转子和级特性线和流场参数的影响；针对转子叶型以轮廓度超差为主的特点，采用S2流面通流计算方法，在设计流量点研究了由轮廓度误差引起的转子叶型最大厚度变化对压气机转子和级性能的影响。结果表明，转子叶片加工误差对压气机堵塞流量、全流量范围内转子和级的压比和效率均有影响，同时改变转静子叶片排出口气流参数的径向分布规律，主要原因为激波位置和强度的变化；在设计流量点，转子和级的压比和效率的变化与最大厚度变化呈负相关趋势，厚度偏差越大性能变化幅度越大；对转子叶片，来流相对马赫数随叶片高度增加而增大，性能对叶型几何误差的敏感性增强，综合压比和效率的变化，中上部叶高范围的轮廓度公差要求应更严格。

Impact of Rotor Blade Manufacturing Variability on 1.5 Stage Transonic Compressor Aerodynamic Performance

Manufacturing variability of compressor blade is inevitable, which may affect the compressor aerodynamic performance to some extent. The inlet 1.5 stage transonic compressor of a gasturbine was selected to investigate the impact of blade manufacturing variability on the aerodynamic performance of transonic compressor. The surface coordinates of machined rotor blades were measured, and the distribution features of manufacuring variability are obtained. For the measured blades, the three dimensional CFD numerical simulation method was adopted to investigate the effects of compound variability including profile, position and twist angle on the performance curves and flow fields of compressor stage and rotor. For the case that manufacturing variability is dominated by profile error, the maximum thickness of blade profile will change correspondingly. The through flow method in S2 surface was utilized to study the effects of maximum thickness change on the compressor stage and rotor performance at design mass flow rate. The results demonstrate that the manufacturing variability of rotor blade will affect the compressor choke mass rate, the total pressure ratio and efficiency of stage and rotor within the whole flow range. The radial profiles of flow parameters at rotor and stator blade outlets are also changed. The results are mainly due to the changes of shock wave position and strength. At design mass flow rate, the changes of total pressure ratio and efficiency of stage and rotor are negatively related with the variation of profile maximum thickness. The changes of performance incease with the increase of thickness error. For rotor blades, the inlet relative Mach number increases from blade root to tip, the sensitivities of performance to geometric variability strengthen. Considering the comprehensive changes of total pressure ratio and efficiency, the tight tolorence of blade profile within middle and tip height shoud be imposed.