An aerodynamic design method for multi-stage axial flow compressors based on key dimensionless load control parameters

Abstract

The purpose of the present invention is to provide an aerodynamic design method for a multi-stage axial flow compressor based on key dimensionless load control parameters, through one-dimensional inverse problem design and characteristic analysis, S2 inverse problem design, blade shape design and three-dimensional CFD analysis and other links Through repeated iterations, the aerodynamic design scheme of the multi-stage axial flow compressor that meets the design index requirements is obtained. The invention realizes the customized design of the internal load of the multi-stage axial flow compressor through three dimensionless parameters of the flow coefficient, the load coefficient and the reaction degree, and effectively solves the problem of design points and low operating conditions in the aerodynamic design of the multi-stage axial flow compressor. The problem of space load matching makes the aerodynamic design of the multi-stage axial flow compressor reach the degree of parameterization and refinement, which improves the design accuracy and shortens the design cycle. At the same time, the method is not limited to multi-stage axial flow compressors of gas turbines, but is also applicable to the aerodynamic design process of various industrial axial flow compressors and aeroengine axial flow compressors / fans.

Description

technical field [0001] The invention relates to a gas turbine design method, in particular to a compressor design method. Background technique [0002] As one of the three most important core components of a gas turbine, the performance of the compressor directly affects whether the economic indicators of the gas turbine can be achieved as designed. In the future, gas turbines need to ensure the continuous improvement of key performance indicators such as efficiency, power, and stability in a wide range of working environments, which puts forward extremely high requirements for the design of compressor components: on the one hand, the level of stage load is increased, on the other hand It is to ensure long-term efficient and stable operation in a wide range of working conditions. Driven by the above needs, it is necessary to explore and develop advanced and efficient compressor aerodynamic design technology and methods to deal with the difficulties and challenges brought by...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a multi-stage axial flow compressor aerodynamic design method based on key dimensionless load control parameters to solve the load matching imbalance problem in the aerodynamic design of the multi-stage axial flow compressor

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