Rotor blade and axial-flow compressor

Abstract

An object of the invention to provide a rotor blade and an axial-flow compressor. The rotor blade is suitable for being mounted on a rotor drum of a rotor of the axial-flow compressor, and includes ablade body, a tenon and a margin plate; for two rotor blades that can be circumferentially adjacent to the rotor drum, a first groove structure of a suction surface portion of the margin plate of oneof the rotor blades and a second groove structure of a pressure surface portion of the margin plate of the other rotor blade are combined and spliced to form a flow channel wall surface between the two rotor blades disposed adjacently in the circumferential direction, and the flow channel wall surface is provided with a plurality of grooves uniformly distributed in a wave shape in the circumferential direction; the grooved extend in a direction from a leading edge to a trailing edge, and the depth of the grooves gradually increases along an extending direction; and end points at which the grooves extend are located on the side wall surface of the margin plate. Presence of the grooves makes the thickness of a boundary layer reduce, thereby reducing a blending and mixing area of interstage leakage and the boundary layer, and so, pneumatic loss caused by the interstage leakage is reduced, and the compressor efficiency and surge margin are improved.

Description

technical field [0001] The invention relates to a rotor blade and an axial flow compressor. Background technique [0002] The axial flow compressor of a gas turbine consists of a rotor and a stator. The rotor is an assembly that rotates at high speed to do work on the airflow, and is used to do work on the gas entering the axial flow compressor. The rotor includes rotor blades. The stator is attached to the casing, including the stator blades. In order to prevent the high-speed rotating rotor blade from colliding with the adjacent stator blade, there is a gap between the edge plate of the rotor blade and the edge plate of the stator blade in the axial direction, which is called the interstage gap. Since there is a certain static pressure difference at the inlet / outlet of the stator blade row, under the effect of this static pressure difference, there will be airflow near the blade crown of the stator blade from the downstream interstage gap of the stator blade through the ...

AI Technical Summary

Problems solved by technology

With the performance requirements of the axial flow compressor, the stage pressure ratio becomes higher and higher, resulting in a higher and higher pressure difference between the stator vane discharge inlet / outlet, which makes it difficult to completely seal the interstage leakage

The airflow leaked between stages often returns to the main channel in a direction close to the vertical direction of the upstream flow, and is mixed with the boundary layer of the upstream flow, which will cause a large loss

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