A three-dimensional blade modeling method for a multistage axial flow compressor based on an end region boundary layer and a blade

Abstract

The invention relates to a three-dimensional blade modeling method for a multistage axial flow compressor based on an end region boundary layer. The three-dimensional blade modeling method is characterized by comprising the following steps of step 1, analyzing the meridian through-flow performance of the prototype multistage axial flow compressor; secondly, extracting the radial gradient of the meridian velocity profile through the through-flow performance in the first step, so that the boundary of a boundary layer is determined, and calculating the displacement thicknesses of the wheel flangeand the boundary layer of the wheel hub side; and step 3, determining initial three-dimensional blade modeling parameters, determining the bending height of the three-dimensional blade according to the relative blade height of the boundary of the corresponding side boundary layer, determining the bending angle of the three-dimensional blade according to the displacement thickness of the corresponding side boundary layer, and forming three-dimensional deformation of a stacking line according to the bending height and the bending angle to obtain the three-dimensional modeling of the blade. Theintegrated modeling design of the three-dimensional blade of the multistage axial flow compressor is realized, the multistage influence of the multistage axial flow compressor is considered, and the flow efficiency of the compressor is improved while the stable work of the compressor is ensured.

Description

technical field [0001] The invention relates to a three-dimensional modeling design method of a blade, in particular to a three-dimensional blade modeling method of a multistage axial flow compressor based on an end zone boundary layer. The invention belongs to the field of axial flow impeller machinery. Background technique [0002] The flow in the end zone of an axial compressor has always been one of the problems that limit the aerodynamic performance of the compressor. How to control the harsh end zone flow environment has become a technical bottleneck in the aerodynamic design of the compressor. In a multi-stage axial flow compressor, unlike single-row diffuser cascades or single-stage compressors, the flow states of each stage are not independent of each other, such as wake, separation and other flow phenomena will propagate to multiple cascade flow channels downstream, called It is the "multi-stage influence" of the multi-stage axial flow compressor. Due to its con...

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Problems solved by technology

[0004] The three-dimensional blade technology has the function of controlling the flow in the end area of ​​the diffuser cascade, but the three-dimensional blade increases the design parameters of the compressor, especially in the multi-stage axial flow compressor, the shape design parameters are multiplied

But at present, most of the three-dimensional blade modeling methods only modify the flow state of a single blade accordingly, and do not take into account the flow characteristics of multi-stage axial flow compressors.

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