Compressor stator cascade with blade root provided with equal-width broken line shaped channels

Abstract

The invention provides a compressor stator cascade with a blade root provided with equal-width broken line shaped channels, relating to passive flow control technology in the technical field of turbo-machinery. The adverse pressure gradient resistance is stronger, Coanda effects are additionally brought and corner separation is better inhibited by forming the equal-width broken line shaped channels in an end wall of the blade root of the compressor stator cascade from a pressure surface to a suction surface, forming high-speed jet by utilizing self-differential pressure of blades, increasing the kinetic energy of low energy fluid at a corner and blowing down airflows on boundary layers of the suction surface and the end wall. The compressor stator cascade is characterized in that the channels are formed in the end wall of the blade root of the compressor stator cascade; the spanwise height is a constant value; the number of the channels can be one or multiple; inlets of the channels are formed in the pressure surface of the cascade and outlets are formed in the suction surface of the cascade; center lines of the channels are multiple broken lines; the two sides of the channels are equally distant from the center lines; and the directions of airflows at the outlets of the channels are basically consistent with the directions of ideal non-separation flow lines. The compressor stator cascade has the beneficial effects of effectively inhibiting corner separation, increasing the cascade flow capacity, reducing the total pressure loss and increasing the pressure 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 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. 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 flow ...

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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