Numerical Simulation Of Axial Clearance Bleeding Effect On A Multistage Axial-flow Compressor Flow-field And Performance

Eruanus solver of Numeca—Fine Turbo software is used in the numerical calculation of this article. 3D Reynold-averaging Navier-Stokes equation is solved with the Jameson finite volume scheme and Spalart-Allmaras turbulence model In relative coordinates system, using explicit Runge-Kutta integration in time to get steady solution. Residual smoothing, local time stepping and a new multi-grid scheme were employed to improve calculative efficiency and accelerate the convergence.Firstly the detailed Numerical Simulation on a tow-stages compressor is done, the numerical results agreed well with experimental test data for the global performance of smooth wall, which ensures the computational reliability and establishes the base on numerical investigating the Axial Clearance Bleeding of a tow-stage Compressor.Because the compressor is tow stages, bleeding calculation of different axial position is done to search the best bleeding position in the numerical Simulation, which is that bleeding equipment is located in some Axial Clearance areas. The numerical results showed that bleeding near the rotor leading edge of second stage can availably extend the operating range of compressor with minimal or no loss in efficiency and total pressure ratio.Boundary layer on the shroud is pumped after bleeding, which restrained the disturbance induced by the interaction of low energy airflow and mainstream, delaying the adverse effect of Clearance flow backwards and improving the mainstream of compressor, weakening the characteristic of leakage vortex, bating the blockage of blade passage at a certain extent. Detailed analysis about the effect of the bleeding on tip flow topologies and the compressor performance is done finally.