Compressor stator cascade with constant depth grooves in end wall

Abstract

The utility model relates to a compressor stator blade cascade with constant-depth grooves in the end wall. It includes a lower end wall, an upper end wall and a plurality of blades arranged side by side between the lower end wall and the upper end wall; the space between two adjacent blades is a cascade channel, the blades are arc plates, the inner arc surface is the pressure surface, and the outer arc The surface is the suction surface, and the inner and outer arc surfaces have two intersection lines in the axial direction. The intersection line near the intake direction is the leading edge line, and the intersection line near the outlet direction is the trailing edge line. The leading edge line and the trailing edge line The distance between them is the chord length of the blade, the height direction of the blade is the span direction, the direction of the connecting line between the same parts of the two blades is the circumferential direction, the length of the connecting line is the cascade pitch, and the direction perpendicular to the circumferential direction in the end wall plane is the axis. At least one groove is formed downwardly on the surface of the lower end wall at the part located in the blade cascade channel. The invention can significantly affect the flow field in the corner area, and under suitable design parameters, the circumferential groove end wall treatment can effectively reduce the total pressure loss coefficient of the compressor stationary blade cascade and improve the cascade diffusion capacity.

Description

technical field

[0001] The invention belongs to the technical field of impeller machinery, and in particular relates to a compressor stator blade cascade with constant-depth grooves on end walls. Background technique

[0002] The requirements of aero-engines for high thrust-to-weight ratio, high efficiency, and high stability margin are driving the development of compressors in the direction of high load and low aspect ratio. The influence of the increase of stage load on the airflow is reflected in the enhancement of the axial reverse pressure gradient and the lateral pressure gradient, which makes the boundary layer low-energy fluid in the blade channel easier to accumulate on the blade suction surface and the end wall corner area, thereby inducing three-dimensional corner zone separation. , block the flow path. The application of low aspect ratio further aggravates the radial proportion of the flow channel occupied by the three-dimensional angular separation. The result...

Images