Abstract The aerodynamic performance and pressure ratio of modern aircraft engine compressor are degrading due to unsteady flow distorted loads complex phenomena in the blade tip. This paper attempts improve axial transonic stage under conditions by incorporating combination groove casing, tip injection technique with surface roughness effects. is performed for Mach number ranging between 0.8 1...

To explain the effect of tip leakage flow on performance an axial-flow transonic compressor, compressors with different rotor clearances were studied numerically. The results show that as clearance increases, intensity is increased, shock wave position moved backward, and interaction between vortex intensified, while boundary layer weakened. Most all, stall mechanisms varying are different. mai...

Abstract Experimental results of a transonic compressor blade pressure loadings and shaft torque measurements are presented in this paper. Data were acquired for the cascade middle being set to number incidence angle offsets simulate phases flutter oscillatory motion. This paper should be viewed as progress report on ongoing larger research effort flow regimes.

The technological process of compressor working blade production from stamping with minimum allowance for machining the part, on 5-axis CNC machine aimed at reducing units equipment has been developed. tooling basing part principle six-point adapted to design tool is realised. geometrical parameters obtained were analysed its mathematical model by 3D scanning method.