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Blade grid for improving pneumatic stability of gas compressor

A technology of stability and compressor, applied in the direction of machines/engines, parts of pumping devices for elastic fluids, mechanical equipment, etc., to achieve the effects of reduced flow loss, improved aerodynamic stability, and enhanced effects

Inactive Publication Date: 2012-05-30
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the defect of poor effect of increasing the aerodynamic stability of the cascade in the prior art, the present invention proposes a cascade to improve the aerodynamic stability of the compressor

Method used

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  • Blade grid for improving pneumatic stability of gas compressor
  • Blade grid for improving pneumatic stability of gas compressor

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Experimental program
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Effect test

Embodiment 1

[0022] Embodiment two

[0023] In this embodiment, the front edges of blades in the same row along the tangential direction of the cascade, that is, the X direction, are arranged differently in front and rear of the cascade axial direction, that is, in the Z direction. Wherein, the leading edge of blade 2 moves back a certain distance relative to the leading edge of blade 1 along the axial direction of the cascade, and the moving distance is 7% of the axial chord length L of blade 1; blade 3 adopts the same blade shape as blade 2, and The distance of the leading edge moving back along the axial direction of the cascade is the same as that of the blade 2 , that is, the moving distance is 7% of the axial chord length L of the blade 1 .

Embodiment 2

[0025] In this embodiment, the front edges of blades in the same row along the tangential direction of the cascade, that is, the X direction, are arranged differently in front and rear of the cascade axial direction, that is, in the Z direction. Wherein, the leading edge of blade 2 moves back for a distance relative to the leading edge of blade 1 along the axial direction of the cascade, and the moving distance is 15% of the axial chord length L of blade 1; blade 3 adopts the same blade shape as blade 2, and The distance of the leading edge moving back along the axial direction of the cascade is the same as that of the blade 2 , that is, the moving distance is 15% of the axial chord length L of the blade 1 .

Embodiment 3

[0027] In this embodiment, the front edges of blades in the same row along the tangential direction of the cascade, that is, the X direction, are arranged differently in front and rear of the cascade axial direction, that is, in the Z direction. Wherein, the leading edge of blade 2 moves back a certain distance relative to the leading edge of blade 1 along the axial direction of the cascade, and the moving distance is 12% of the axial chord length L of blade 1; blade 3 adopts the same blade shape as blade 2, and The backward moving distance of the leading edge along the axis of the cascade is the same as that of the blade 2 , that is, the moving distance is 12% of the axial chord length L of the blade 1 .

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Abstract

The invention relates to a pneumatic blade grid layout for improving the pneumatic stability of a gas compressor. Every three adjacent blades in the same blade row are a blade group, the axial position of the front edge of a first blade (1) is taken as a standard, and the front edge of a second blade (2), which is adjacent to the first blade (1), moves rearwards to 7 to 15 percent of the axial chord length L of the first blade (1) along the axial direction of a blade grid according to the positioned standard; the front edge of a third blade (3), which is adjacent to the second blade (2), and the front edge of the second blade (2) are positioned on the same position on the axis direction of the blade grid, and the third blade (3) and the second blade (2) adopt the same blades; and other blades on the same blade row are distributed according to the manner. In the invention, three different air channels are formed in the same blade row, and the air current flow has unique characteristicswhich are different from the prior art, therefore, the invention can improve the pneumatic stability of the gas compressor better and has the capacities of increasing the pneumatic load of the bladesand reducing the flow loss.

Description

1. Technical field [0001] The invention relates to the field of axial-flow impeller machinery, and relates to a cascade for improving the aerodynamic stability of a compressor. 2. Background technology [0002] Modern high thrust-to-weight ratio aviation gas turbine engines require fewer stages of compressors and high aerodynamic stability. However, for the aerodynamic design of compressors in the prior art, while reducing the number of stages of compressors and increasing the aerodynamic load of blades, it often causes compressor The aerodynamic stability of the machine is reduced. For this reason, various methods have been adopted in the aerodynamic design and structural design to improve the aerodynamic stability of the compressor. The existing conventional axial flow compressor blades adopt a completely axisymmetric and evenly distributed design scheme. When the inlet airflow angle of attack is large, the airflow boundary layer on the back surface of each blade will be...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/34F04D29/66
Inventor 刘前智廖明夫王四季王俨剀杨伸记
Owner NORTHWESTERN POLYTECHNICAL UNIV
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