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A Multistage Compressor Stable Working Margin Adjustment System

A technology for regulating system and stable operation, applied in gas turbine devices, mechanical equipment, jet propulsion devices, etc., can solve problems such as the reduction of engine economy, and achieve the effect of ensuring economy and improving operation reliability.

Active Publication Date: 2017-07-25
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the interstage gas release at the design speed will reduce the economy of the engine due to the release of a certain amount of gas.

Method used

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  • A Multistage Compressor Stable Working Margin Adjustment System
  • A Multistage Compressor Stable Working Margin Adjustment System
  • A Multistage Compressor Stable Working Margin Adjustment System

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Embodiment Construction

[0044] In order to make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be described in further detail below with reference to the accompanying drawings and embodiments. It should be noted that, the following descriptions are only preferred embodiments of the present invention, which do not limit the protection scope of the present invention.

[0045] It should be noted that the implementations not shown or described in the accompanying drawings are the forms known to those of ordinary skill in the art. In addition, the directional terms mentioned in the following embodiments, such as "up", "down", "front", "rear", "left", "right", "top", "bottom", etc., are only for reference the direction of the figure. Accordingly, the directional terms used are illustrative and not limiting of the present invention.

[0046] like figure 1 , 2 As shown in the figure, the multi-stage compressor stable working margin adjustme...

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Abstract

The invention relates to a stable working margin adjusting system of a multistage compressor, and is suitable for a double-duct turbofan engine. The system comprises a high-pressure intake pipe, a two-position three-way electromagnetic valve, an acting cylinder and an exhaust port; an intake end of the high-pressure intake pipe is communicated with high-pressure air currents of the multistage compressor; the exhaust port is formed in a compressor shell on a medium-pressure stage; a control device acquires working condition state information of the multistage compressor, and controls the two-position three-way electromagnetic valve according to the acquired information; when the multistage compressor is located in a non-designed working condition, a piston in the acting cylinder upwards moves to drive an exhaust cover plate in a base to upwards move so as to communicate an inner duct runner with an outer duct runner, and the air currents in the inner duct runner flow into the outer duct runner to realize interstage exhaust; and when the multistage compressor is located in a designed working condition, the piston in the cylinder downwards moves to drive the exhaust cover plate in the base to downwards move to close exhaust of the compressor.

Description

technical field [0001] The invention relates to a system for adjusting the stable working margin of a multi-stage compressor. In aero-engines, the multi-stage compressor is the main structural form of its high-pressure compressor, and the multi-stage compressor often has insufficient stable working margin under non-design conditions. The interstage deflation is an effective means to improve the stable working margin of the compressor. Based on this actual demand, the present invention invents a regulating system that can realize this function, which is especially suitable for small and medium-sized aviation turbofans with double ducts. engine. Background technique [0002] A turbofan aeroengine is generally composed of a fan, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine, of which the high-pressure compressor is the main boosting component in the aeroengine. As aero-engines have higher and higher requirements for thrus...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C9/18
CPCF02C9/18
Inventor 赵胜丰卢新根李伟阳诚武韩戈朱俊强
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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