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Axial flow compressor stator blade arrangement style

A technology for axial flow compressors and stator blades, which is applied to components of pumping devices for elastic fluids, mechanical equipment, non-variable pumps, etc., and can solve the problem of increased axial size of blade rows, difficulty in realization, and flow splitting The structural strength of the blade is not easy to meet the requirements, etc., to achieve the effect that is easy to achieve

Inactive Publication Date: 2010-05-12
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] In order to overcome the disadvantages that the staggered layout of the blade rows increases the axial size of the blade rows, the structural strength is not easy to meet the requirements when the splitter blades are used, and it is difficult to realize in engineering, the present invention proposes a method that can effectively reduce compression. Arrangement form of stator blade row for machine weight

Method used

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  • Axial flow compressor stator blade arrangement style
  • Axial flow compressor stator blade arrangement style
  • Axial flow compressor stator blade arrangement style

Examples

Experimental program
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Effect test

Embodiment 1

[0021] This embodiment is a single-stage axial flow compressor with 60 stator blades. In practice, the stator blades of the compressor are made into 30 wide blades 1 and 30 narrow blades 2, and the number of blades in the blade row remains constant. The size of the wide blade 1 is the same as the size of the conventional design when it is evenly arranged, and the geometric size of the narrow blade 2 is reduced by 6% compared with the wide blade 1, and the wide blade 1 and the narrow blade 2 are alternated along the circumferential direction, that is, the X direction Arranged to form a row of stator blades. When arranged, the axial position of the leading edge of each adjacent wide and narrow blade has a δ misalignment, so that the trailing edge of the blade in the same row of stator blades is at the same axial position, while the front The edges are not at the same axial position; the axial position of the leading edge of the narrow blade 2 is staggered backward from the axial ...

Embodiment 2

[0024] This embodiment is a two-stage axial flow compressor, with 57 stator blades in the first stage and 74 stator blades in the second stage.

[0025] In practice, the first-stage stator blades of the compressor are made into 29 wide blades 1 and 28 narrow blades 2, the axial chord length of the wide blades 1 is the same as the conventionally designed size when they are uniformly arranged, and the geometric dimensions of the narrow blades 2 Compared with the wide blade 1, it is reduced by 10%; when arranging, one side of the two wide blades 1 is arranged adjacent to each other along the circumferential direction, that is, the X direction, and the other side is respectively adjacent to the narrow blade; The blades are arranged in such a way that wide blades 1 and narrow blades 2 are alternately arranged to form a row of stator blades. When arranged, the axial positions of the leading edges of all wide blades 1 are the same, and the axial positions of the leading edges of all ...

Embodiment 3

[0029] This embodiment is a single-stage axial flow compressor with 67 stator blades. In practice, the stator blades of the compressor are made into 34 wide blades and 33 narrow blades, the number of blades in the blade row remains unchanged, and the geometric dimensions of the narrow blades 2 are reduced by 12% compared with the wide blades 1; , along the circumferential direction, that is, the X direction, first arrange one side of the two wide blades 1 adjacent to each other, and the other side is adjacent to the narrow blade respectively; then arrange the remaining blades alternately according to the wide blade 1 and the narrow blade 2 Arranged in a manner to form a row of stator blades. When arranged, the axial positions of the leading edges of all wide blades 1 and wide blades 1 are the same, and the axial positions of the leading edges of all narrow blades 2 are also the same, while the axial positions of the leading edges of adjacent wide blades and narrow blades Ther...

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Abstract

The invention provides a distributing method for the static vane rows of a compressor. Aiming at overcoming the shortcomings that the axial size is large and the weight is high in the prior art, the invention processes the static vanes into wide vanes 1 and narrow vanes 2 whose axial length of all sectional vane shapes from the vane root to the vane tip is reduced for 5-15 percent than the wide vanes 1. The ratio of the Delta to the axial chord of the wide vane S is 5-15 percent; the two kinds of vanes are arrayed in intervals on the same static vane row, a derangement of Delta is arranged between the front edges of the neighboring vanes, and the rear edges are aligned on the same axial position. An interspace C and an interspace D are respectively formed on the front edges between the wide vanes and the neighboring two narrow vanes 2, and the ratio of the C to the D is 0.82 to 1.2. The other static vane rows can be arrayed according to the method, and the vane airflow passages formedwhen the wide and the narrow vanes are alternatedly arrayed are in two different forms. Due to the adopted technical proposal, the invention can effectively reduce the weight of the static vane rows,and can reduce the weight of the compressor greatly.

Description

(1) Technical field [0001] The invention relates to the field of axial-flow impeller machinery, and relates to an arrangement form of stator blade rows that can reduce the weight of a compressor. (2) Background technology [0002] Weight and aerodynamic stability are one of the important performance parameters of axial flow compressors. To this end, people have taken many measures in terms of materials, processing, aerodynamic design and structural design to reduce the weight of the compressor and improve the aerodynamic stability of the compressor. [0003] The blades of the existing axial flow compressor adopt a completely axisymmetric and evenly distributed design, that is, regardless of the compressor rotor blade row or the stator blade row, the same blades are used in the circumferential direction according to the circumferential uniformity and the same axial position layout arrangement. For such an axisymmetric homogeneous layout, weight savings can only be achieved ...

Claims

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Application Information

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