Basov Y. Gas Turbine Engines High-Loaded Axial Compressor Stages Rotor Blades Gas-Dynamic Design Method

The object is aviation gas turbine engine high-loaded axial compressor stages rotor blade rows flow. The aim is creation of gasdynamic designing method of high-loaded axial compressor stages rotor blade rows. The methods are design-theoretical ones. The novelty consists in high-loaded axial compressor stages rotor gasdynamic designing method proposition, new data about summary parameters and flow structure modes changing features in three high-loaded axial compressor stages acquisition, blade geometrical parameters influencing on flow features and summary gasdynamic parameters determination, testing gasdynamic calculation method development for its diversification to Mach number 1.4-1.6. the results are geometrical parameters of perspective aviation engines compressor rotors with the high values of total pressure rise obtaining, the quality of designing improvement. The branch is aviation engine engineering.