Abstract
The phenomenon of separated flow hysteresis in the process of the streamlining the axial compressor of gas-turbine engines is considered. Generalised results of research on the occurrence of hysteresis in the aerodynamic performance of compressor grids and its influence on the performance of the bladed disks of compressors that operate in real conditions of periodic circular non-uniformity are demonstrated.
Highlights
IntroductionThe operation of gas-turbine engine compressor aerofoil grids at supercritical angles of attack (angles of flow acceleration) is connected with the appearance of intensive areas of flow separation on the blade surfaces
The operation of gas-turbine engine compressor aerofoil grids at supercritical angles of attack is connected with the appearance of intensive areas of flow separation on the blade surfaces
Research of the occurrence of this process and development of flow separation modes in grids demands solving tasks connected with predicting the aforementioned occurrence of flow separation modes in compressor grids, defining ways to extend the range of the non-separated streamline of the bladed disks of compressors, and increasing their gas-dynamic stability margins (Chang 1979; Tereshchenko et al 2005, 2010; Lastivka 2011)
Summary
The operation of gas-turbine engine compressor aerofoil grids at supercritical angles of attack (angles of flow acceleration) is connected with the appearance of intensive areas of flow separation on the blade surfaces. The structure and characteristics of separated flows significantly depend on their kinematic performances – velocity, angles of attack, and flow parameters such as pressure, density and temperature – and it depends on the direction of their change within the interval of certain values. This means that at the same ensemble of parameters different aerodynamic performances can emerge. One of the reasons for this phenomenon is aerodynamic hysteresis brought about by the flow structure reforming when there is a change in at least one parameter (such as velocity of non-disturbed flow, angle of attack, or Reynolds’s number) and under conditions of unsteady flow–frequency and amplitude of oscillations
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