Axial flow compressor stator blade arrangement style

An axial flow compressor and stator vane technology, which is applied to the components of the pumping device for elastic fluid, mechanical equipment, non-variable-capacity pumps, etc. It is not easy to meet the requirements, the realization is difficult, etc., to achieve the effect that is easy to achieve

Inactive Publication Date: 2008-04-30
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] 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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Embodiment 1

[0023] 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, the number of blades in the blade row remains unchanged, the size of the wide blades 1 is the same as the conventionally designed size when they are evenly arranged, and the narrow blades The geometric size of 2 is 6% smaller than that of wide blade 1, and the wide blade 1 and narrow blade 2 are alternately arranged along the circumferential direction, that is, the X direction, to form a row of stator blades. When arranging, 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, but the leading edge is not at the same axial position The distance δ that the axial position of the narrow blade 2 leading edge is staggered backward than the axial pos...

Embodiment 2

[0026] 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.

[0027] 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

[0031] 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 is an arrangement form of compressor stator vane rows. In order to overcome the shortcomings of large axial size and heavy weight in the prior art, the present invention makes the stator blades into wide blades (1) and the axial chord length of each cross-sectional airfoil from the blade root to the blade tip is reduced relative to the wide blade (1). 5% to 15% smaller narrow blade (2); the ratio of δ to the axial chord length S of the wide blade is 5% to 15%; the two blades are arranged at intervals in the same row of stator blades, and the front of the adjacent blade There is a dislocation of δ between the edges, while the trailing edge is aligned at the same axial position; the gaps C and D are formed between the wide blade (1) and the two adjacent narrow blades (2) at the leading edge, and The ratio of C to D is 0.82-1.2. Arrange other stator vane rows in this way, so that the vane airflow channels formed when the wide and narrow vanes are arranged alternately are in two different forms. Due to the technical solution adopted by the invention, the weight of the stator vane row is effectively reduced, so that the weight of the compressor is significantly reduced.

Description

[0001] (1) Technology area [0002] 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 [0003] 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. [0004] 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 ac...

Claims

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Application Information

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