Axial-flow compressor stator blade

Abstract

The invention relates to an axial-flow compressor stator blade comprising a blade root part, a blade middle part and a blade tip part, wherein the blade root part rightly bends at 15-25 degrees in tangential direction; the stacking line of the blade middle part is a straight line; and the blade tip part rightly bends at 15-25 degrees in tangential direction. The stator blade adopts a three-dimensional design structure with the blade root and the blade tip symmetrical up and down and rightly bending in tangential direction, and can effectively inhibit stalling at a corner area of a hub of a compressor first stage stator with low flow range ahead of a stalling point, on the premise of not reducing efficiency of the compressor and not changing the loss margin of the compressor basically under high flow, thus obviously reducing the air flow loss of the compressor within the range of flow and further improving the efficiency of the compressor well.

Description

technical field [0001] The invention relates to a stator blade, in particular to a first-stage stator blade for a two-stage low-speed axial flow compressor. Background technique [0002] As a device that works on gas to increase its pressure, the axial flow compressor is widely used in military and civilian fields such as aviation, ground, ships, missiles, and gas turbines. With the continuous development of the aviation industry, the performance requirements of aero-engines continue to increase. As one of the three core components of aero-engines, the compressor needs to provide a larger pressure ratio and have higher efficiency. [0003] As the pressure ratio of the compressor increases, the reverse pressure in the blade channel increases, and the boundary layer separation in the blade channel becomes more intense, especially the expansion of the three-dimensional stall range in the hub-corner region. It can lead to a great reduction in the efficiency of the compressor, a...

AI Technical Summary

Problems solved by technology

[0003] As the pressure ratio of the compressor increases, the reverse pressure in the blade channel increases, and the boundary layer separation inside the blade channel becomes more intense, especially the three-dimensional stall range in the hub-corner region expands, and the It can lead to a great reduction in the efficiency of the compressor, and more importantly, it will cause the entire compressor to enter a stall and surge state, which will bring serious consequences

[0004] The existing two-stage low-speed axial flow compressor test bench has a design total pressure ratio of 1.035 and a flow rate of 25kg / s at the design point. The compressor has a problem that the angular separation is not obvious when the flow rate is large, and the loss is small. Small flow range at stall point 1st stage stator blade root and tip section, especially the root section, hub-corner zone stall is very severe, resulting in a sharp drop in efficiency

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