Recontouring of Jet Engine Compressor Bladesby Flow Simulation

[摘要] In modern jet propulsion systems the core engine has an essential influence on the total engine performance. Especially the high pressure compressor plays an important role in this scheme. Substantial factors here are losses due to tip clearance effects andaerodynamic airfoil quality. During flight operation the airfoils are subject to wear andtear on the leading edge. These effects cause a shortening of the chord length and theleading edge profiles become deformed. This results in a deterioration of the engineefficiency performance level and a reduced stall margin.The paper deals with the re-contouring of the leading edges of compressor airfoilsby application of a new developed method for the profile definition. The commonprocedure of smoothing out the leading edges manually on a wheel grinding machinecan not provide a defined contour nor a reproducible result of the overhaul process. Inorder to achieve optimized flow conditions in the compressor blade rows, suitableleading edge contours have to be defined for the worn airfoils. In an iterative processthe flow behavior of these redesigned profiles is checked by numerical flow simulationsand the shape of the profiles is improved. The following machining of the new definedleading edge contours is achieved on a grinding station handled by an appropriatelyprogrammed robot.

[学科分类] 力学，机械学