Gas compressor stator blade grid with equal-depth grooves formed in end walls

Abstract

The invention discloses a gas compressor stator blade grid with equal-depth grooves formed in the end walls. The gas compressor stator blade grid with the equal-depth grooves formed in the end walls comprises a lower end wall, an upper end wall and a plurality of blades arranged between the lower end wall and the upper end wall side by side; the space between every two adjacent blades is a blade grid channel, the blades are arc-shaped plates, the inner arc faces are pressure faces, the outer arc faces are suction faces, the inner arc faces and the outer arc faces are provided with two intersecting lines in the axial direction, each intersecting line close to the air inlet direction is a leading edge line, each intersecting line close to the outlet direction is a trailing edge line, the distance between each leading edge line and the corresponding trailing edge line is the blade chord length, the height direction of the blades is the spanwise direction, the direction of a connecting line between the same parts of every two blades is the circumferential direction, the length of the connecting line is the blade grid pitch, and the direction perpendicular to the circumferential direction in the end wall plane is the axial direction; and the portions, located in the blade grid channels, of the surface of the lower end wall are sunken downwards to form at least one groove. Accordingto the gas compressor stator blade grid with the equal-depth grooves formed in the end walls, the flow field of the corner area can be obviously influenced, and under proper design parameters, the total pressure loss coefficient of the gas compressor stator blade grid can be effectively reduced through circumferential groove type end wall treatment, and the diffusion capacity of the blade grid isimproved.

Description

technical field [0001] The invention belongs to the technical field of impeller machinery, in particular to a compressor stator vane cascade with equal-depth grooves on the end wall. Background technique [0002] The requirements of aero-engines for high thrust-to-weight ratio, high efficiency, and high stability margin are pushing the compressor to develop in the direction of high load and low aspect ratio. The impact of the increase of stage load on the air flow is reflected in the enhancement of the axial reverse pressure gradient and the transverse pressure gradient, making it easier for the low-energy fluid in the boundary layer in the blade passage to accumulate on the suction surface of the blade and the corner region of the end wall, thereby inducing three-dimensional corner separation , to block the flow path. The application of low aspect ratio further increases the radial ratio of the three-dimensional corner separation. The result of flow separation is the gene...

AI Technical Summary

Problems solved by technology

It can be seen that the research on flow control in the diagonal region is far from over, and further exploration and new control methods are still needed.

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