Aero-engine compression component adjustable guide vane adjusting method for coping with temperature distortion

An adjustment method and engine technology, applied in the direction of machines/engines, mechanical equipment, non-variable pumps, etc., to achieve the effects of improving the ability to resist temperature distortion, improving the design level, and improving performance

Active Publication Date: 2021-02-02
AECC SHENYANG ENGINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of this application is to provide a method for adjusting the adjustable guide vane of the compression part of the aeroengine to deal with temperature distortion, so as to solve or alleviate at least one of the problems in the background technology

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  • Aero-engine compression component adjustable guide vane adjusting method for coping with temperature distortion
  • Aero-engine compression component adjustable guide vane adjusting method for coping with temperature distortion
  • Aero-engine compression component adjustable guide vane adjusting method for coping with temperature distortion

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Embodiment Construction

[0020] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application.

[0021] In order to overcome the shortcomings in the prior art, this application provides a method based on the design level of the existing compression components, by changing the adjustment method of the adjustable guide vanes of the compression components to improve the engine’s resistance to temperature distortion. It can work stably under the condition of temperature distortion.

[0022] The technical scheme of the method for adjusting the adjustable guide vane of the compression part of the aero-engine proposed in this application to deal with temperature distortion is as follows:

[0023] The main compression parts of the engine, such as fans or compressors, the change of the adjustable guide vane angl...

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Abstract

The invention provides an aero-engine compression component adjustable guide vane adjusting method for coping with temperature distortion. The method includes the steps that at least two temperature sensors are arranged in different positions in the circumferential direction of an engine inlet or a compression component inlet and are used for measuring the temperature of the engine inlet or the compression component inlet; the difference value between the highest value and the lowest value of the temperature sensors is judged, if the difference value between the highest value and the lowest value is larger than a preset value, the numerical value of the temperature sensor with the highest value in the temperature sensors is used as control input, and the adjustable guide vane angle of thecompression component is adjusted; and if the difference value between the highest value and the lowest value is smaller than the preset value, the average value of the temperature sensor is used as control input, and the adjustable guide vane angle of the compression component is adjusted. According to the method, the temperature distortion resistance of the engine can be improved, the performance sacrifice is small, stability expansion can be conducted only when temperature distortion occurs, and the performance of other flight positions, except the temperature scene, in the full envelope can be improved.

Description

technical field [0001] The present application belongs to the technical field of aero-engines, and in particular relates to a method for adjusting an adjustable guide vane of a compression part of an aero-engine to deal with temperature distortion. Background technique [0002] During the take-off or flight of the aircraft, due to the operation of the engine, a low-pressure area will be generated near the air inlet of the aircraft, and the nearby air will be sucked in. When there is a heat source in the air, the air sucked into the engine inlet will be distorted in space and timing, that is, Inhomogeneity in space and step in timing. After the temperature distortion is superimposed on the pressure distortion of the inlet itself, it will have an important impact on the performance and stability of the engine. In severe cases, it will even cause the engine to surge and affect flight safety. [0003] There are many scenarios that generate temperature distortion, for example: w...

Claims

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Application Information

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IPC IPC(8): F04D27/00
CPCF04D27/002F04D27/001
Inventor 刘永泉谢业平张志学梁彩云金海施磊任智博何佳倩潘宝军
Owner AECC SHENYANG ENGINE RES INST
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