Gas compressor stator blade root slotting method based on optimization algorithm

A compressor and cotyledon technology, applied to components, stators, mechanical equipment, etc. of pumping devices for elastic fluids

Active Publication Date: 2016-07-13
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in terms of flow control, especially in the aspect of adding auxiliary equipment to control the flow in the compressor, the current research methods have limitations, and the

Method used

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  • Gas compressor stator blade root slotting method based on optimization algorithm
  • Gas compressor stator blade root slotting method based on optimization algorithm
  • Gas compressor stator blade root slotting method based on optimization algorithm

Examples

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Embodiment Construction

[0034] Specific embodiments of the present invention will be described below in conjunction with the accompanying drawings.

[0035] Such as figure 1 As shown, for a compressor stator cascade with slotted S-shaped blade roots, a tapered channel 4 is provided at the end wall 3 of the cascade root from the pressure surface 1 to the suction surface 2 of the cascade.

[0036] Such as figure 2 As shown, according to the flow field of the NACA prototype stator cascade, the slot geometry of the reference point is initially determined by the 4° angle of attack separation.

[0037] Combined with the actual geometry of the channel, the parameter ranges and reference values ​​of the channel are shown in the table below:

[0038]

Minimum value (mm)

Reference value (mm)

Max(mm)

S1

Channel inlet position

25

40

60

S2

Channel exit position

40

60

80

L1

Channel inlet length

15

35

55

L2 ...

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Abstract

The invention discloses a method for optimizing gas compressor stator blade root slotting channel geometry based on an optimization algorithm, and relates to the technical field of optimization algorithms and impeller mechanical flow control.The method aims at obtaining optimal blade root channel geometry through optimization calculation so that the angle area separation control effect of a force suction face can be optimal.By means of the gas compressor stator blade root slotting method based on the optimization algorithm, all design parameters of blade root channels can be subjected to coupling calculation and analysis, the optimal channel control effect is proposed based on an optimization calculation result, the coupling effect between the geometrical parameters of the channels can be comprehensively considered, and thus it is avoided that only changes of a single parameter or a few of parameters are calculated in flow optimization control.The optimization algorithm is a multi-target function optimization algorithm based on a non-domination ranking genetic algorithm, the S-shaped channels contracting to a force suction surface from a pressure surface are subjected to optimization calculation, the optimization parameters include inlet positions and outlet positions of the channels, lengths and channel heights, and a target function includes a blade grid total pressure loss coefficient, a static pressure raising coefficient and a blade grid channel blockage coefficient.The gas compressor stator blade root slotting method has the advantages that an optimization method and a blade grid flow control method are combined, channel geometry is optimized on the condition that the original blade grid blade shape is fixed, and thus the control effect is optimal.

Description

technical field [0001] The invention relates to an optimization algorithm and a flow control of a compressor stator cascade, in particular to a flow control scheme for slotting of a compressor stator cascade that suppresses separation of compressor stator angular regions, and belongs to the passive flow control technology in the technical field of turbomachinery. Background technique [0002] Among the internal flow of turbomachinery, the most complicated flow is the flow in the corner area. The end wall boundary layer, blade boundary layer, various vortex structures and their interactions exist in the corner flow between the suction surface and the end wall, which are the main factors that cause the performance deterioration of the compressor stator cascade. The flow separation in the corner area will lead to channel blockage, blade load and diffuser capacity reduction, resulting in total pressure loss and efficiency reduction, and in severe cases, it will cause engine surg...

Claims

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Application Information

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IPC IPC(8): F01D9/02F01D25/04F04D29/54F04D29/68
CPCF04D29/682F04D29/684F01D9/02F01D25/04F04D29/541F04D29/681F05D2250/20
Inventor 柳阳威孙槿静陆利蓬唐雨萌
Owner BEIHANG UNIV
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