Abstract
Abstract As the core component of modern gas turbines, multistage axial compressors have a decisive influence on the performance of gas turbines. This paper proposes a multi-stage axial compressor characteristic calibration method based on one-dimensional average streamline method. Firstly, according to the physical laws followed by the multi-stage axial compressor, the aerodynamic analysis method of axial compressors is established which based on the one-dimensional average streamline method. Secondly, develop an automatic calibration method for the cascade performance model, use genetic algorithms to establish a complete blade wake Momentum thickness coefficient scalar database to realize the automatic calibration of compressor characteristics. This method has fast calculation speed and versatility. It can predict, encrypt and extrapolate compressor characteristics. It can be used to predict the characteristics of inlet guide vanes and stationary vanes when they are adjustable, or to calculate the overall performance without experimental data or CFD data.
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