缺陷叶片对跨音速压气机转子气动性能影响

Impact of Defective Blades on Aerodynamic Performance of Transonic Compressor Rotor

基于Hicks-Henne三维高阶延拓函数,提出了一种表征服役条件下由于积垢、腐蚀或磨损等因素造成压气机叶片表面几何缺陷的三维通用几何参数化建模方法,并以Rotor37为例,重点研究了叶片表面局部凸起缺陷对跨音速压气机转子气动性能和内部流动的影响。结果表明:叶片表面不同位置凸起缺陷的存在,使得Rotor37多变效率下降1.0%~1.3%;当表面凸起缺陷位于吸力面50%叶高、50%弦长附近时,激波诱导边界层分离现象明显加重,致使气动性能衰减更为剧烈。该研究对于深入认识服役条件下的压气机气动性能变化具有一定的理论价值。

Based on a 3D higher-order Hicks-Henne function, a generalized 3D geometry pa- rameterization method is established to describe the defects distributed on the compressor blade surface due to fouling, corrosion and abrasion within service. In particular, the impact of local defect on the performance and internal flow for Rotor 37 is investigated. The results show that the polytropic efficiency of Rotor37 is decreased by 1.0% 1.3% due to the presence of local convex defect on the blade surface. When the convex defect is located at about 50% of the blade height and 50% of the chord on the suction side, the shock-induced flow separation becomes obviously more serious, causing much increased performance degradations for the compressor. This work is of cer- tain theoretical value for a deep understanding of the performance variations of in-service compressors.