Louver distribution of raising pneumatic stability

A technology of stability and layout, applied in the field of turbomachinery, can solve problems such as the potential limitation of mining

Inactive Publication Date: 2007-05-02
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But for the existing symmetrical uniform cascade, the potential that can be tapped is very limited

Method used

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  • Louver distribution of raising pneumatic stability
  • Louver distribution of raising pneumatic stability
  • Louver distribution of raising pneumatic stability

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0014] In this embodiment, the front edges of the same row of blades along the circumferential direction, that is, in the X direction, are arranged alternately in an axial direction, that is, in the Z direction.

[0015] The leading edge of blade 2 in the axial position moves backward relative to the leading edge of blade 1 in the normal position along the axis of the compressor for a certain distance, and the moving distance is 7% of the axial chord length of the blade, wherein the axial chord length is taken as the normal position The width of the blade in the axial direction. In this embodiment, the profile of the blade 2 at the backward position is exactly the same as that of the blade 1 at the normal position, and the installation angle changes to 0°.

Embodiment 2

[0017] In this embodiment, the front edges of the same row of blades along the circumferential direction, that is, in the X direction, are arranged alternately in an axial direction, that is, in the Z direction.

[0018] The leading edge of blade 2 in the axial position moves backward relative to the leading edge of blade 1 in the normal position along the axis of the compressor for a certain distance, and the moving distance is 13% of the axial chord length of the blade, wherein the axial chord length is taken as the normal position The width of the blade in the axial direction, and the blade 2 rotates 0.5° around the leading edge point toward the direction of the blade pot, that is, the installation angle defined by the axial Z direction is reduced by 0.5°. In this embodiment, the profile of the blade 2 in the backward position is exactly the same as that of the blade 1 in the normal position.

Embodiment 3

[0020] In this embodiment, the front edges of the same row of blades along the circumferential direction, that is, in the X direction, are arranged alternately in an axial direction, that is, in the Z direction.

[0021] The leading edge of blade 2 moves backward in the axial position relative to the leading edge of blade 1 in the normal position and moves backward for a certain distance along the axial direction of the compressor. The moving distance is 10% of the axial chord length of the blade, and the axial chord length is taken as the normal position The width of the blade in the axial direction, and the blade 2 rotates 3.0° around the leading edge point toward the direction of the blade pot, that is, the installation angle defined by the axial Z direction is reduced by 3.0°. In this embodiment, the profile of the blade 2 in the backward position is exactly the same as that of the blade 1 in the normal position.

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Abstract

A vane placement of compressor for improving its pneumatic stability and avoiding the rotational stall features that the front ends of the vanes in same row are alternatively and axially arranged in back-and-forth direction. The staggered size is the 5-15% of the axial chord of each vane. The variation range of axial installation angle of the vane moved backward is 0 - -3 deg.C.

Description

(1) Technical field: [0001] The invention relates to the field of impeller machinery, and relates to a cascade aerodynamic layout that can improve the aerodynamic stability of a compressor. (two) background technology: [0002] Aerodynamic stability is one of the most important performance parameters for axial and centrifugal compressors. For this reason, people have adopted many design schemes in aerodynamic design and structural design to improve the aerodynamic stability of the compressor. The blades of existing axial flow compressors adopt a completely axisymmetric and evenly distributed design, that is, regardless of the compressor rotor blades or stator blades, the same primitive blade shape is used in the circumferential direction and arranged in the exact same axial position. of. [0003] For this axisymmetric uniform layout, when the inlet airflow angle of attack is large, the airflow boundary layer on the back surface of each blade will be separated at the same t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/66F04D29/34F04D29/54
Inventor 刘前智廖明夫
Owner NORTHWESTERN POLYTECHNICAL UNIV
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