Koorosh K. Selection technique of rational parameters highly-loaded blade rows of gas-turbine engine axial-flow compressor

The dissertation work is devoted to development of selection technique of rational parameters highly-loaded blade rows of gas-turbine engine axial-flow compressor. Application of this technique during designing and modernization engines will be allow to increasing axial compressor performances. Carried out analysis of losses structure in compressor blade rows which is showing considerable three dimensional structure of flow in gas channel and indicated that three dimensional boundary layer on the blade had very highly influence on losses structure. The dissertation investigation was directed on decreasing of losses. Features of flow in compressor blade rows and calculation problem of real gas flows at transonic speeds is reviewed. Applying a method of mathematical simulation for reaching the purpose of activity, requirement to a package of the computational programs of flowing part profiling an aero-engine is reviewed. The formulated main requirements, with which one should be contented with the numerical method for its successful applying at calculation of viscosity compressed flows in stages of an axial-flow compressor. The algorithm of computational grid adapting for calculation of three-dimensional flows in stages of an axial-flow compressor is reviewed. The technique of the geometrical shape correction of axial-flow compressor stages is designed, which one includes the registration of losses distribution on an altitude of a blade, and compressor blades shape change by activity. With its help the correction of design inlet and outlet flow angle of blade rows by criterion of a minimum of losses is held, at the registration of change of the blade shape on an altitude.