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Improved compressor blade and achieving method thereof

A compressor and improved technology, applied in mechanical equipment, machines/engines, liquid fuel engines, etc., can solve problems such as the loss of compressor rotor blades and other problems, and achieve the effect of reducing flow loss

Active Publication Date: 2016-02-17
SHANGHAI JIAO TONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this device only considers the noise problem in the axial flow wind turbine environment, and does not solve the loss problem in the compressor rotor blade environment

Method used

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  • Improved compressor blade and achieving method thereof
  • Improved compressor blade and achieving method thereof
  • Improved compressor blade and achieving method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0031] This embodiment realizes the improved compressor blade in the following ways:

[0032] 1) For example figure 1 The prototype moving blade shown is parametrically modeled, and the prototype moving blade includes: leading edge 1, trailing edge 2, blade top 3 and blade root 4, and the radial stacking method of blades is determined as trailing edge stacking, that is, Ensure that the curve of the trailing edge 2 of the simulated moving blade remains unchanged from that of the prototype moving blade;

[0033] 2) According to the definition of the center arc: the locus of the center of the common tangent circle tangent to the pressure surface arc and the suction surface arc of the airfoil, the reference center arcs of the different blade height cross-section airfoils of the prototype moving blade are obtained, and the reference center The length of the arc is L, and the size of L changes with the change of the height H of the leading edge;

[0034] 3) Introduce the wave-shap...

Embodiment 2

[0046] The difference between this embodiment and embodiment 1 is:

[0047] The amplitude A is taken as 0.05L, and the wavelength W is taken as 0.1H.

[0048] Through numerical calculation, the improved compressor blade with this value reduces the relative total pressure loss coefficient by 3%, reduces the flow loss in the top area of ​​the blade, and thus improves the performance of the compressor.

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Abstract

The invention discloses an improved compressor blade and an achieving method thereof. A movable blade body comprises a front edge and a tail edge. The leaf height of the front edge is H, and a corrugated knotted protrusion structure is arranged on the top of the front edge. The curve form of the corrugated knotted protrusion structure is a cubic spline curve, and amplitudes of crests and troughs of the corrugated knotted protrusion structure are different. The corrugated knotted protrusion structure is arranged on the top of the front edge within the range of 0.76 H-H. The wave amplitude of points on the curve is A, and the length of a benchmark mean camber line corresponding to the points is L, wherein A is larger than 0 and smaller than or equal to 0.05 L, the wavelength is W, and the W is larger than 0 and smaller than or equal to 0.1 H. According to the structural characteristic of front edge knotted protrusions of the flipper of the humpback, corrugated knotted protrusions with a certain wave amplitude and wavelength are arranged on the top area of the front edge of the movable blade body, the low resistance characteristic of the corrugated knotted protrusions is utilized, the flow loss on the top area of the blade is reduced, and the performance of a compressor is improved.

Description

technical field [0001] The invention relates to a technology in the field of compressors, in particular to an improved compressor blade for reducing losses and a realization method thereof. Background technique [0002] Modern aeroengines require compressors with higher aerodynamic loads and fewer stages. In the process of compressor design, the increase of the aerodynamic load of the blade is often accompanied by the increase of the compressor loss, and the secondary flow phenomenon of the compressor (such as the tip leakage flow) will cause the loss of the local area to increase. Excessive loss will greatly reduce the performance of the compressor, resulting in very adverse consequences. Therefore, reducing losses is an important task in the process of developing high-performance gas turbines. [0003] The methods of reducing losses in compressor design can be divided into two categories: active control and passive control. Compared with active control, passive control ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/38G06F19/00
CPCF04D29/384F05D2240/303F05D2250/183
Inventor 郑覃朱铭敏羌晓青滕金芳
Owner SHANGHAI JIAO TONG UNIV
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