End-to-end design of multistage high-pressure axial compressor for a promising aviation gas turbine engine

Abstract

Abstract The paper describes the results of an end-to-end design of a multistage high-pressure axial compressor for a promising aircraft engine. The design included the steps of initial design and detailed fine-tuning of the working process using three-dimensional numerical modelling. The initial design included the steps of flow path shape determination, design thermodynamic calculation, and one-dimensional gas dynamic calculation at the mid-diameter and height of the flow path. Statistical processing of parameters of known compressors was used to select parameters during the initial compressor design. The initial design was performed for several compressor configurations differing in the main design parameters: type of flow path, number of stages, speed and others. Three-dimensional modelling and comprehensive comparison of working process parameters were performed for the most promising of the obtained variants. On its basis, the most promising variant was selected, for which the subsequent refinement using three-dimensional numerical modelling was carried out. As a result of compressor design, all required parameters were achieved.