Factors determining the loss of energy of compressor stage gas turbine engine based on flow parameters

Abstract

In this work numerical modeling of a three-dimensional viscous current in blade cascade of the axial compressor of low pressure of the gas-turbine engine is executed. Gasdynamic computation of a flow in the first step of the compressor in non-stationary three-dimensional statement by means of a program complex F is carried out. For modeling of the turbulent flows which are realized in the majority of practical applications, the most widespread technique is application of Reynolds-averaged Navier–Stokes equations (RANS) supplemented by a certain model of turbulence. The two-equation differential k-ω SST Menter’s turbulence model is used. The initial equations are integrated in number by means of the iterative obvious and implicit differential scheme of the second order of approximation which obvious operator is based on the ENO scheme of Harten, and implicit approximation is realized by means of the scheme of Bima-Uorminga-Stegera. The structure of a stream in the axial compressor is analyzed. The gas-dynamic structure of a flow has changeable character on blade height from a root to the periphery. Effect of radial clearance, vortex wake, back-flow allow to receive real flow pattern.