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A flow separation active control structure, method and application

An active control, flow separation technology, applied in the direction of machines/engines, liquid fuel engines, components of pumping devices for elastic fluids, etc., can solve the problem of reducing the overall efficiency and working stability of the engine, and cannot meet the needs of future development , limiting the performance of gas turbine engines, etc.

Active Publication Date: 2022-03-04
AERO ENGINE ACAD OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] The design of modern aircraft is rapidly developing in the direction of stealth, high mobility, and flight-engine integration. Traditional passive design methods are increasingly unable to meet the needs of future development.
[0003] There are a large number of flow separation phenomena in aero-engines, such as the flow separation in the S-shaped inlet, the corner separation flow in the compressor / turbine and the leakage flow in the tip clearance, and the flow separation in the high and low pressure rotation stages of the compressor. Separation phenomenon reduces the overall efficiency and working stability of the engine, limiting the further improvement of gas turbine engine performance

Method used

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  • A flow separation active control structure, method and application
  • A flow separation active control structure, method and application
  • A flow separation active control structure, method and application

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0056] refer to Figure 2-Figure 5 , an active control structure for flow separation in a gas turbine engine, including a fluid oscillator array 1, the fluid oscillator array 1 includes N fluid oscillators 2, N≥1; the fluid oscillator 2 includes a fluid oscillator flow channel 20, N fluid oscillator flow channels 20 form a fluid oscillator array flow channel; the fluid oscillator array flow channel is arranged in the main channel wall of the engine; the inlet of the fluid oscillator 2 is connected to the gas source 3 through the control valve 4; the fluid oscillator 2 The outlet is arranged at the leading edge of the flow separation point to be controlled.

[0057] The air source 1 is an external air source or a high-pressure air source from the rear-stage compressor. By adjusting the pressure at the inlet of the fluid oscillator 2, the flow channel 20 of the fluid oscillator generates a corresponding self-excited oscillation, and the fluid oscillator 2 The required operating...

Embodiment approach

[0060] refer to Figure 4 with Figure 5 , the direction of the outlet jet of the fluid oscillator of the fluid oscillator array 1 and the controlled main flow direction in the main channel (the main flow direction in the cascade) form a certain angle β; The walls are parallel, and the outlet air flow channel of the fluid oscillator 2 forms an included angle β with the plane where the flow channel of the fluid oscillator array is located; 0°≤β≤180°. At this time, from Figure 4 The middle C direction is perpendicular to the wall surface of the main channel and the flow channel 20 of the fluid oscillator at the same time, and the fluid oscillator array channel located inside the wall surface of the main channel and a series of discrete micropores located at the wall surface of the main channel can be seen at the same time. Such as Figure 5 shown.

[0061] With this embodiment, since the plane where the fluid oscillator array channel is located is parallel to the main chann...

Embodiment 2

[0070] refer to Figure 2-Figure 5 , based on the active control structure of flow separation in Embodiment 1, this embodiment proposes a method for active control of flow separation, including the following steps:

[0071] According to the range of flow separation that needs to be controlled, select a corresponding number of fluid oscillators 2, and set a corresponding number of fluid oscillator channels 20 in the main channel wall of the engine to construct any of the above active control structures for flow separation;

[0072] Adjust the control valve 4 to control the connection between the inlet and the air source 3, or change the pressure of the inlet, so as to form a jet with a set oscillation frequency and amplitude at the outlet of the fluid oscillator 2 to delay or eliminate the flow Separation happens.

[0073] In this embodiment, when the range of flow separation to be controlled is relatively large, the number of fluid oscillators in the fluid oscillator array ca...

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PUM

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Abstract

The present disclosure provides a flow separation active control structure, method and application. The flow separation active control structure includes a fluid oscillator array, and the fluid oscillator array includes N fluid oscillators, N≥1; the fluid oscillator It includes a fluid oscillator flow channel, N said fluid oscillator flow channels form a fluid oscillator array flow channel; said fluid oscillator array flow channel is set in the wall of the main channel of the engine; said fluid oscillator inlet and air source pass through The control valve is connected; the outlet of the fluid oscillator is arranged at the leading edge of the controlled flow separation point. The flow separation active control structure and method of the present disclosure can be actively adjusted according to actual working conditions, and can adapt to different working conditions. At the same time, by directly injecting a suitable disturbance mode in the flow environment to couple with the intrinsic mode of the system, a very small disturbance can be applied to the flow field near the main channel wall to control the main flow with large momentum.

Description

technical field [0001] The present disclosure relates to flow separation control of aero-engines, and in particular to a flow separation active control structure, method and application in a gas turbine engine. Background technique [0002] The design of modern aircraft is rapidly developing in the direction of stealth, high mobility, and flight-engine integration. Traditional passive design methods are increasingly unable to meet the needs of future development. [0003] There are a large number of flow separation phenomena in aero-engines, such as the flow separation in the S-shaped inlet, the corner separation flow in the compressor / turbine and the tip clearance leakage flow, and the flow separation in the high and low pressure rotation stages of the compressor. The separation phenomenon reduces the overall efficiency and working stability of the engine, and limits the further improvement of the performance of the gas turbine engine. Contents of the invention [0004] ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C3/04F02C7/00F04D29/38F04D29/54
CPCF02C3/04F02C7/00F04D29/542F04D29/388F04D29/384
Inventor 王士奇罗斌张亚华贾志刚
Owner AERO ENGINE ACAD OF CHINA