Shelkovsky M. Increasing of the gas-turbine engine compressors efficiency by their aerodynamic improvement based on the three-dimensional flow analysis

The dissertation solves the problem of gas turbine engine compressors efficiency increasing by a complex variation of blade profiles — their lean, chord variation, using three-dimensional controlled diffusion, S-shaped profiles, based on the calculation of the three-dimensional viscous flow and the theory of experiment planning. Kompress 2.0 software for blades profiling and ANSYS CFX software for the threedimensional viscous flow calculation were used to implement such calculations. An optimal design methodology for multistage axial compressor blade vanes profiling was developed, taking into account limitations, in the form of the hybrid aerodynamic problem solution. In this methodology the designing with the definition of geometric forms was carried out as a solution of an inverse problem with further optimality verification and output aerodynamic characteristics calculations by a direct method. In particular, new parametric models of rotor and stator blades were adapted for their aerodynamic optimization; an analytical dependence for lean shape of stator blades based on the radial flow non-uniformity was obtained; a new analytical dependencies obtaining method for optimal incidence angles, deviation angles, stall criteria and loss coefficients in multistage axial compressor blade vanes was proposed as an approximating functions composition; algorithms and programs for blades profiling with S-shape and thickness change have been developed; the simplified method of compressor stages characteristics modeling on changing geometric blade parameters based on the greek-latin square method was developed by the direct problem solving. The presented calculation and theoretical analysis of the gas-turbine engine compressor form formation was used in the designing of three multistage axial compressors - three-stage, six-stage and ten-stage. The preparation schemes for multistage compressors test rig researches have been developed; the methodology for determining of the flow parameters along the multistage compressor flow path based on the direct measurements results during its test rig researches was created. An original aerodynamic test rig was designed for experimental efficiency verification of the proposed stator blade vanes lean form, and a methodology for studying of the flow parameters in the sector stator blade vanes model was created. Aerodynamic optimization of the multistage experimentally investigated compressors using the suggested approaches allowed to obtain an efficiency of the highpressure compressor stages 0.92-0.93 and to increase the efficiency of multi-stage axial compressors by 1-2,4 %.