Gas compressor stator blade root slotting method based on optimization algorithm

Abstract

The invention discloses a method for optimizing gas compressor stator blade root slotting channel geometry based on an optimization algorithm, and relates to the technical field of optimization algorithms and impeller mechanical flow control.The method aims at obtaining optimal blade root channel geometry through optimization calculation so that the angle area separation control effect of a force suction face can be optimal.By means of the gas compressor stator blade root slotting method based on the optimization algorithm, all design parameters of blade root channels can be subjected to coupling calculation and analysis, the optimal channel control effect is proposed based on an optimization calculation result, the coupling effect between the geometrical parameters of the channels can be comprehensively considered, and thus it is avoided that only changes of a single parameter or a few of parameters are calculated in flow optimization control.The optimization algorithm is a multi-target function optimization algorithm based on a non-domination ranking genetic algorithm, the S-shaped channels contracting to a force suction surface from a pressure surface are subjected to optimization calculation, the optimization parameters include inlet positions and outlet positions of the channels, lengths and channel heights, and a target function includes a blade grid total pressure loss coefficient, a static pressure raising coefficient and a blade grid channel blockage coefficient.The gas compressor stator blade root slotting method has the advantages that an optimization method and a blade grid flow control method are combined, channel geometry is optimized on the condition that the original blade grid blade shape is fixed, and thus the control effect is optimal.

Description

technical field [0001] The invention relates to an optimization algorithm and a flow control of a compressor stator cascade, in particular to a flow control scheme for slotting of a compressor stator cascade that suppresses separation of compressor stator angular regions, and belongs to the passive flow control technology in the technical field of turbomachinery. Background technique [0002] Among the internal flow of turbomachinery, the most complicated flow is the flow in the corner area. The end wall boundary layer, blade boundary layer, various vortex structures and their interactions exist in the corner flow between the suction surface and the end wall, which are the main factors that cause the performance deterioration of the compressor stator cascade. The flow separation in the corner area will lead to channel blockage, blade load and diffuser capacity reduction, resulting in total pressure loss and efficiency reduction, and in severe cases, it will cause engine surg...

AI Technical Summary

Problems solved by technology

However, in terms of flow control, especially in the aspect of adding auxiliary equipment to control the flow in the compressor, the current research methods have limitations, and the use of optimization algorithms for flow control has not been widely used, especially for plasma excitation and boundary layer pumping. , vortex generator and other control technologies

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