Optimization of geometry blade for modern high pressure compressor

Abstract

An integration of CFD-3D codes and modern efficient methods of optimization is essential for the contemporary compressors improvement. In order to solve optimization tasks the insular information exchange circle was created. The data circulates between the mathematical model of the stream in a compressor, the algorithm of compressor’s geometry construction based on parameterization and algorithm of optimization itself. The mathematical model of the compressor covers procedures of mesh generation and calculations using CFD code. This model has been verified by experimental data.A high-pressure compressor of multi regime gas turbine engine for supersonic civil aircraft has been considered as the object of our study. The goal of the research was to increase the efficiency in the design point with the ensured preset gas dynamic parameters under other modes. The variables for optimization task were installation angles and the shape of the middle line of the profile in three sections along the height of the compressor rotor and stator blades. The total amount of independent variables was 72. As a result of the study the optimal geometry for the stator and rotor blades in supersonic aircraft engine has been obtained. The initial project efficiency had been improved by 1-2%, while stability margin remained constant.