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

Abstract

The invention provides a compressor stator cascade with a blade root provided with equal-width circular arc 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 circular arc 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 stator cascade and outlets are formed in the suction surface of the cascade; center lines of the channels are shaped like circular arcs; the two sides of the channels are equally distant from the center lines; and the outlets in the side walls of the channels are tangent to the downstream wall of the suction surface of the cascade. 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] In the internal flow of the turbomachinery, the most complicated flow is the flow in the corner area. There are end wall boundary layer, blade boundary layer, various vortex structures and their interactions in the corner area flow between the suction surface and the end wall. The main factor causing 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 loss in ...

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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