Multi-dimensional collaborative design method for multi-stage axial flow compressor of ship gas turbine

Abstract

The invention aims to provide a multi-dimensional collaborative design method for a multistage axial flow compressor of a ship gas turbine, and the method comprises the following steps: repeatedly iterating links such as one-dimensional design and analysis, two-dimensional design, quasi-three-dimensional design, blade modeling design, quasi-three-dimensional analysis, full-three-dimensional analysis, collaborative design and the like; and obtaining the aerodynamic design scheme of the multistage axial flow compressor of the ship gas turbine meeting the design index requirements. The method hasthe characteristic of cross-dimension design, design parameters of different dimensions can be interactively used, only three-dimensional CFD calculation with few times is needed to initialize the loss model, and after the initialization work of the loss model is completed, the loss and performance parameter information of the compressor can be obtained in a quasi-three-dimensional design stage without three-dimensional CFD calculation, so that the design efficiency of the compressor is improved. Therefore, a high-quality compressor aerodynamic design scheme can be quickly completed, a largeamount of calculation time is saved, the design period is effectively shortened, and the method is very suitable for engineering design application.

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 marine gas turbine, the performance of the compressor directly affects the realization of the economic indicators of the marine gas turbine. With the continuous improvement of the performance indicators of marine gas turbines, the modern marine gas turbine compressors are developing in the direction of high pressure ratio, high efficiency, and large surge margin. In the future, the marine gas turbine compressor must have excellent performance of high efficiency and high stable working range in the whole range of working conditions, in order to meet the increasing performance indicators of future marine gas turbines, which puts forward higher requirements for the aerodynamic design of the compressor. [0003] The research and development history of foreign marine gas tur...

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Problems solved by technology

[0004] The purpose of the present invention is to provide a multi-dimensional collaborative design method for a multi-stage axial flow compressor of a ship gas turbine to solve the aerodynamic design problem of a multi-stage axial flow compressor of a ship gas turbine

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