Compressor stator cascade with oblique small ribs on suction surface

Abstract

The invention discloses a gas compressor stator cascade with inclined small ribs on a suction surface. A plurality of inclined small rib groups which are sequentially connected end to end and are alternately distributed in a left-inclined manner and a right-inclined manner are arranged near a tail edge on the suction surface from an end wall in the spanwise direction; and each inclined small rib group consists of a plurality of inclined small ribs which are arranged in parallel at intervals along the chordwise direction, so that a spanwise array is formed. The invention has the following beneficial effects: by arranging the inclined small ribs at the trailing edge of the suction surface of the stator cascade, on one hand, airflow in a separation area can be stirred by trailing vortex generated by the inclined small ribs, so that high-energy airflow at the upper part of a boundary layer can be mixed with low-energy airflow near a wall to increase momentum and energy of fluid near the wall, thereby delaying separation; on the other hand, the trailing vortex generated by the small ribs is used for blocking propagation of low-energy fluid in the corner area to the spanwise suction surface, and therefore the purposes of controlling corner area separation and improving the performance and stability of the gas compressor are achieved.

Description

technical field [0001] The invention belongs to the technical field of aviation gas turbine engines, in particular to a compressor stator vane cascade with oblique small ribs on the suction surface. Background technique [0002] The compressor is the core compression component of the aviation gas turbine engine, and its performance has a crucial impact on the work and performance of the aviation gas turbine engine. With the increase of the thrust-to-weight ratio of the aviation gas turbine engine, the single-stage load of the compressor is constantly increasing, and at the same time, the corner separation is induced to a greater extent. The flow separation in the corner area will lead to channel blockage, blade load and decrease in diffuser capacity, resulting in total pressure loss and efficiency decrease, and in severe cases, it will cause stall and surge of aerogas turbine engine. Therefore, trying to suppress the corner separation of the compressor is very important to ...

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Problems solved by technology

However, the traditional passive control method represented by vortex generators will also introduce additional losses while obtaining aerodynamic gains. Therefore, how to find a balance between aerodynamic gains and additional losses has been widely concerned by academia and industry. topic

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