Axial flow compressor surge boundary calculation method based on full three-dimensional numerical simulation

Abstract

The invention provides an axial flow compressor surge boundary calculation method based on full three-dimensional numerical simulation. The axial flow compressor surge boundary calculation method comprises calculation grid model setting and numerical calculation method setting. Calculation grid model setting and numerical calculation method setting are respectively based on IGG / AutoGrid 5 softwareand ANSYS / CFX software. Grid data transmission is carried out between the two different kinds of software through a grid converter self-programming program. The whole calculation process integrates the advantages of different software, and aims to provide an appropriate grid model and an appropriate numerical calculation method for accurately predicting the surge boundary of the gas compressor. The grid generated by the grid setting method provided by the invention is high in quality, the number of grid nodes is small, and the actual geometric structure characteristics of some air compressorsare comprehensively considered. The numerical value setting method provided by the invention is not influenced by the unsmooth profile of the blade profile structure of the gas compressor, and is relatively good in robustness and wide in applicability. The method can be widely applied to the pneumatic design process of turbomachinery such as an axial-flow compressor, an axial-flow compressor, anaxial-flow fan and an axial-flow fan.

Description

technical field [0001] The invention relates to a method for calculating the surge boundary of an axial flow compressor based on full three-dimensional numerical simulation, which belongs to the field of aerodynamic design of turbomachinery and can be widely used in axial flow compressors, axial flow compressors, axial flow fans and axial flow fans, etc. Turbomachinery aerodynamic design process. Background technique [0002] As one of the core components of aero-engines and ground gas turbines, the stability of the compressor directly affects the safe operation of the engine. Surge, as an unstable working condition that easily occurs during the operation of the compressor, is extremely harmful. Therefore, how to accurately predict the compressor surge boundary and avoid the occurrence of compressor surge is extremely important in the design process. [0003] The currently commonly used compressor surge boundary prediction methods can be roughly classified into three categ...

AI Technical Summary

Problems solved by technology

The larger the number of grids, the calculated efficiency of the compressor is often higher than the test results, and the more the number of grids, the multi-stage compressor will also face problems such as difficult calculation and difficult convergence

In order to solve the long-term problem that turbomachinery aerodynamic designers cannot accurately predict the surge boundary of the compressor, the present invention proposes a calculation method for the surge boundary of the axial flow compressor based on full three-dimensional numerical simulation

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