Multistage axial flow compressor aerodynamic design method based on key dimensionless load control parameters

Abstract

The invention aims to provide a multistage axial flow compressor aerodynamic design method based on key dimensionless load control parameters, which comprises the following steps of: repeatedly iterating links such as one-dimensional inverse problem design and characteristic analysis, S2 inverse problem design, blade modeling design, three-dimensional CFD analysis and the like; and obtaining a multi-stage axial flow compressor aerodynamic design scheme meeting design index requirements. Customized design of the internal load of the multi-stage axial flow compressor is achieved through three dimensionless parameters including the flow coefficient, the load coefficient and the reactivity, and the problem of space load matching between design points and low working conditions in pneumatic design of the multi-stage axial flow compressor is effectively solved; and the pneumatic design of the multistage axial flow compressor achieves the parameterization and refinement degree, the design precision is improved, and the design period is shortened. Meanwhile, the method is not limited to a multi-stage axial flow compressor of a gas turbine, but also suitable for the pneumatic design process of various industrial axial flow compressors and aero-engine 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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