Computational study of gas dynamic influence on the flow in lattice of airfoils

Abstract

A computational study of flow in lattices of airfoils of compressor of gas turbine engines with gas-dynamic effect on the aerodynamic traces behind outbound edges of input directing device was conducted. Summarized results of computational study in the form of dependency of levels of unevenness of flow from the intensity of gas-dynamic effect on the flow in a wide range of Reynolds numbers at fixed Mach numbers, the distances from the outbound edges and options for placement of slits for blowing additional air mass were presented. Using the results of computational study and comparative analysis with the results of some well-known experimental studies the data about the aerodynamic structure of the aerodynamic traces behind the axial compressor stator elements with the gas-dynamic effect on it were received and the efficiency of the gas-dynamic effect on the aerodynamic traces to improve the parameters and characteristics of the compressor elements of gas turbine engines was determined. Established that gas-dynamic effect on the flow in lattices of aerodynamic profiles is characterized by uneven flow reduction to minimum values of in a range of intensity values of blowing more air mass in the boundary layer. For Mach numbers of 0.15 – 0.45 at low, compared to the profile chord, distance from the original edge are actually centered on the axis of the trace. With increase of subsonic speeds and higher values of Reynolds numbers the opposite effect is observed – level unevenness of the flow begins to increase