Moving blade row layout capable of improving axial compressor aerodynamic performance

An axial flow compressor and rotating blade technology, which is applied to machines/engines, components of pumping devices for elastic fluids, mechanical equipment, etc., can solve the problems of rising flow loss at design point and limited improvement of turning angle, etc. Achieve the effects of improved flow conditions, no reduction in aerodynamic stability, and large boost ratio

Inactive Publication Date: 2010-12-01
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, when the consistency increases to a certain value, the effect of improving the turning angle at the design point with a small angle of attack is very limited, and the flow loss near the design point increases significantly

Method used

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  • Moving blade row layout capable of improving axial compressor aerodynamic performance
  • Moving blade row layout capable of improving axial compressor aerodynamic performance
  • Moving blade row layout capable of improving axial compressor aerodynamic performance

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] The arrangement of the blades in the rotating blade row in this embodiment is: N=2, in the circumferential direction X of the blade row, a blade group is formed by 5 adjacent blades, and the fifth blade is the next blade group. The first blade 1; in the same blade group, the second blade 2 is located on the side of the back surface of the first blade 1, the third blade 3 is located on the side of the back surface of the second blade 2, and the fourth One blade 4 is located on the side of the back surface of the third blade 3, the first blade 1 is located on the side of the back surface of the fourth blade 4 in the previous blade group, and so on. The position of the compressor axis Z of the leading edge of each blade in a blade group constitutes a triangular wave. The leading edge of the first blade 1 in the blade group is located at the peak of the triangular wave, and the leading edge of the third blade 3 is located at the trough of the triangular wave. , The period T ...

Embodiment 2

[0031] The arrangement of the blades in the row of rotating blades in this embodiment is: N=3, in the circumferential direction X of the blade row, 7 adjacent blades form a blade group, and the seventh blade is the next blade group. The first blade 1; in the same blade group, the second blade 2 is located on the side of the back surface of the first blade 1, the third blade 3 is located on the side of the back surface of the second blade 2, and the fourth One blade 4 is located on the side of the back surface of the third blade 3, the fifth blade 5 is located on the side of the back surface of the fourth blade 4, and the sixth blade 6 is located on the back surface of the fifth blade 5. Side, the first blade 1 is located on the side of the back surface of the fourth blade 6 in the previous blade group, and so on. The position of the compressor axis Z of the leading edge of each blade in a blade group constitutes a triangular wave. The leading edge of the first blade 1 in the bl...

Embodiment 3

[0034] In this embodiment, the arrangement of the blades in the rotating blade row is: N=4, in the circumferential direction X of the blade row, a blade group is formed by 9 adjacent blades, and the ninth blade is the next blade group. The first blade 1. In the same blade group, the second blade 2 is located on the side of the back surface of the first blade 1, the third blade 3 is located on the side of the back surface of the second blade 2, and the fourth blade 4 is located on the Three blades 3 are on the back surface side of the blade, the fifth blade 5 is located on the back surface side of the fourth blade 4, the sixth blade 6 is located on the back surface side of the fifth blade 5, and the seventh blade The blade 7 is located on the side of the back surface of the sixth blade 6, the eighth blade 8 is located on the side of the back surface of the seventh blade 7, and the first blade 1 is located on the eighth blade 8 in the previous blade group. The back surface side ...

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PUM

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Abstract

The invention provides a moving blade row layout capable of improving axial compressor aerodynamic performance. Axial compressor blades are periodically arranged along the peripheral direction X; each period is composed of 2N numbered blade paths, and the ligature of the axial positions of the front edges of the blades arranged in each period forms a triangular wave; the front edge of the first blade (1) and the front edge of a (2N+1)th blade in each period are positioned on the wave crest of the triangular wave; and the front edge of the (N+1)th blade is positioned on the wave trough of the triangular wave. Under the condition that the bending of the blades is constant and aerodynamic stability is not lowered and can be properly improved, the moving blade row has improved boost ratio, increased blockage flow and unreduced efficiency under the state of small angle of attack of a design point. The compressor of the invention can choose a zero-incidence even negative incidence state to serve as the aerodynamic design point, can obtain the higher boost ratio and efficiency near the design point and has bigger stability margin of the compressor.

Description

1. Technical Field [0001] The invention relates to the field of axial flow impeller machinery, in particular to a rotary blade row layout for improving the aerodynamic performance of an axial flow compressor. 2. Background technology [0002] Improving the aerodynamic performance of compressors is a requirement for the aerodynamic design of modern high-performance axial compressors. Improving the aerodynamic performance of compressors includes improving the design boost ratio, efficiency and aerodynamic stability. Generally speaking, the existing conventional axial compressor blade row adopts a completely axisymmetric and uniform layout design, that is, all blades in the same row have the same geometric shape and size, and are arranged in the axial direction of the compressor. Same, the distance between adjacent blades in the circumferential direction is the same. For this kind of conventionally arranged compressor rotating blade row, when the design aerodynamic load is higher a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/38
Inventor 刘前智廖明夫王俨剀王四季
Owner NORTHWESTERN POLYTECHNICAL UNIV
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