Blade root slotting gas compressor stator with gradual-contraction changes of slot span-wise height

Abstract

The invention discloses a blade root slotting gas compressor stator with gradual-contraction changes of the slot span-wise height, and relates to the driven flowing control technology in the technical field of turbo machines. A slot of the equivalent-width span-wise height gradual-contraction type is formed from a pressure face to a suction face at the blade root of a blade grid of the gas compressor stator, and the streaming pressure difference of a blade is utilized for forming jet flow to restrain and delay flow separation. One or more slots are formed in the blade root of the blade grid of the gas compressor stator. A slot inlet is formed in the pressure face of the blade grid of the stator, and a slot outlet is formed in the suction face of the blade grid. The widths of the slots are equivalent, the slot inlet is higher than the slot outlet, the contraction slot is formed in the slot height direction, and the distance between the upper wall face and the end wall of each slot is in smooth transition. The blade root slotting gas compressor stator has the beneficial effects that kinetic energy of low-energy fluid of boundary layers at the end wall and the suction face outlet of the slot is supplemented through the jet flow of the slot, airflow of the boundary layer of the suction face of the blade grid and the boundary layer of the end wall are blown away, and flowing separation is restrained and delayed, so that the pressure expansion capacity of the portion behind a blade grid channel is recovered.

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 cascade. 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. ...

AI Technical Summary

Problems solved by technology

The above-mentioned technology has at least the following disadvantages: For engineering applications, the connection arc of the slotting scheme is relatively random, and the slot width changes irregularly, which is not easy to process; the spanwise height of the slot is a fixed value, and the jet velocity of the slot is not easy to adjust; the control parameters Too many, and lack of design criteria, the control scheme is also difficult to optimize the design

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