Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas

A technology of axial flow compressor and plasma, applied in the direction of pump control, machine/engine, mechanical equipment, etc., to achieve the effect of suppressing flow separation, improving efficiency and low energy consumption

Inactive Publication Date: 2012-07-25
AIR FORCE UNIV PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It can solve problems such as rapid active control and excitation that cannot be solved or difficult to solve by other flow control methods, and provides a good basic condition for realizing real-time adaptive flow control

Method used

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  • Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas
  • Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas
  • Method for exciting and controlling gas flow of stator blade end wall of axial-flow compressor by aid of plasmas

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Embodiment Construction

[0026] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

[0027] Step 1: Lay a plasma pneumatic actuator on the end wall of the stator vane channel of the axial flow compressor, such as figure 1 The end wall of the stator blade marked in . The leading edge and the trailing edge of the electrode of the plasma pneumatic exciter are respectively flush with the leading edge and the trailing edge of the stator blade, and the direction of the electrode is parallel to the middle arc of the stator blade;

[0028] The electrodes of the plasma pneumatic excitation electrodes are copper electrodes, and the electrodes are separated by insulating materials, and the insulating materials are polyimide. The layout of the plasma pneumatic excitation electrodes is as follows figure 2 As shown, the upper surface electrode width d 1 2mm, the electrode width d on the lower surface 2 is 2mm, the distance between the upper and lower surf...

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Abstract

The invention relates to a method for exciting and controlling gas flow of the stator blade end wall of an axial-flow compressor by the aid of plasmas, which is characterized by including the steps: laying a plasma pneumatic exciter on the stator blade passage end wall of the axial-flow compressor, wherein the front edge and the tail edge of an electrode of the plasma pneumatic exciter are level to the front edge and the tail edge of a stator blade respectively, and the direction of the electrode is parallel to a mean camber line of the stator blade; when an engine controller detects flow instability indication, loading electric signals to the electrode of the plasma pneumatic exciter by employing a pulse plasma power source; and when the engine controller detects disappearance of flow instability indication, sending out control signals, and closing the plasma pneumatic exciter. The control method is capable of effectively suppressing stator blade angle area flow separation of the axial-flow compressor, short in exciting response time and wide in bandwidth, and has an important role in reduction of stator blade wake pitot loss and improvement on stability and efficiency of the compressor.

Description

technical field [0001] The invention belongs to the active flow control technology in the field of gas turbine engines, and relates to a method for using plasma excitation to control gas flow at the end wall of a vane end wall of an axial flow compressor, and a plasma pneumatic actuator used in the method. Background technique [0002] The axial flow compressor is one of the core components of the aviation gas turbofan engine, and its development trend is higher pressure ratio, efficiency and stability, and fewer stages. Due to the strong pressure gradient in the flow direction and the lateral flow of the boundary layer in the blade channel, the low-energy fluid accumulates in the stator blade suction face / end wall corner region, thereby forming a significant corner region flow separation. On the one hand, corner separation limits the increase of compressor load and static pressure lift capacity, on the other hand, it leads to the decrease of compressor efficiency and stall ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D27/00
Inventor 吴云李应红赵小虎李军贾敏
Owner AIR FORCE UNIV PLA
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