Compressor and compressor blades

Abstract

The purpose of the present invention is to provide a compressor blade, which can obtain relatively better aerodynamic performance compared with existing compressor blades. Another object of the present invention is to provide a compressor comprising the above-mentioned compressor blade. The compressor blade for achieving the aforementioned purpose comprises a blade body and an edge plate connected to the blade top or blade root of the blade body, the joint between the blade body and the edge plate is transitioned by a rounded corner, and the rounded corner A small chamfering radius is adopted at the leading edge of the airfoil, and the chamfering radius gradually increases from the leading edge of the airfoil to the trailing edge of the blade. Wherein, the fillet has a connection length L with the end wall surface of the edge plate, a height H connected with the airfoil, an included angle α formed with the end wall surface, and an included angle β formed with the surface of the airfoil, From the leading edge to the trailing edge, L, H, α, β gradually increase.

Description

technical field [0001] The present invention relates to compressors and blades thereof. Background technique [0002] In the actual axial flow compressor, due to the influence of processing technology and strength factors, the root of the moving blade and the root tip of the stationary blade are usually chamfered, such as figure 1 as well as figure 2 The three-dimensional schematic view and the top view schematic view of the existing blades are respectively shown. It can be seen from the figure that figure 1 as well as figure 2 The blades 8 shown in all have chamfers 9, and these chamfers 9 are symmetrical structures as shown in the figure. image 3 A schematic diagram is defined for the shape of the existing rounded corner of the blade. The shape of the chamfer 9 is as shown in the figure, which is equal to the included angle R formed by the end wall 91 and the airfoil surface 92 . [0003] According to the research of the inventor, after adding the chamfered structur...

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Problems solved by technology

[0003] According to the research of the inventor, after adding the chamfered structure of the moving and static blades to the multi-stage axial compressor, under the action of the chamfering, the distribution of the vortex system in the cascade flow field changes, the vortex in the upper and lower channels migrates to the direction of the middle blade span, and the end The strength of the corner vortex at the wall increases, and the secondary flow loss increases. When the chamfer radius increases to a certain extent, the flow rate and performance of the compressor will decrease significantly

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