Compressor stator cascade with equal-width broken-line grooves at the blade root

Abstract

The utility model relates to a stator vane cascade of a compressor with equal-width broken-line grooves on the blade root, and relates to passive flow control technology in the technical field of impeller machinery. Its purpose is to open equal-width broken-line grooves from the pressure surface to the suction surface at the root end wall of the stator cascade of the compressor, use the pressure difference of the blade itself to form a high-speed jet, increase the kinetic energy of the low-energy fluid in the corner area, and blow off the suction surface and end. The airflow of the surface layer attached to the wall makes the ability to resist the reverse pressure gradient stronger, and additionally brings the Coanda effect, which better inhibits the separation of the corner area. The channel is located at the root end wall of the stator blade cascade of the compressor, and the spanwise height is a constant value. There can be one or more channels. The inlet of the channel is located on the pressure surface of the cascade, and the outlet is located on the suction surface of the cascade. The center line is a multi-segment broken line and the two side walls of the channel are equidistant from the center line, and the airflow direction at the outlet of the channel is basically consistent with the direction of the ideal non-separation flow line. The invention has the beneficial effects of effectively suppressing the separation of corner areas, increasing the flow capacity of the cascade, reducing the total pressure loss, and increasing the diffusion capacity.

Description

technical field [0001] The invention relates to the flow control of a stator cascade of a compressor, in particular to a flow control scheme for slotting a blade root of a stator cascade of a compressor to suppress the angular separation of the compressor stator, and belongs to the passive flow control technology in the technical field of impeller machinery. Background technique [0002] Among the internal flow of turbomachinery, the most complicated flow is the flow in the corner region. 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. 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 surge. The flo...

AI Technical Summary

Problems solved by technology

The above-mentioned technology has at least the following disadvantages: For engineering applications, the slotting scheme is relatively idealized, and the connecting arc is relatively random, which is not easy to process; especially the direction of the formed jet velocity cannot be controlled, and the angle with the mainstream direction may be large, resulting in " "step" flow to produce negative effects, making it difficult to optimize the design of the control scheme

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