Adjustable guide vane adjustment method for aero-engine compression components in response to temperature distortion

A technology of aero-engines and adjustment methods, which is 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: 2022-07-15
AECC SHENYANG ENGINE RES INST
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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 art

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  • Adjustable guide vane adjustment method for aero-engine compression components in response to temperature distortion
  • Adjustable guide vane adjustment method for aero-engine compression components in response to temperature distortion
  • Adjustable guide vane adjustment method for aero-engine compression components in response to temperature distortion

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Embodiment Construction

[0020] In order to make the implementation purpose, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.

[0021] In order to overcome the shortcomings of the prior art, the present application provides a method for improving the temperature distortion resistance level of the engine by changing the adjustment method of the adjustable guide vanes of the compression component based on the design level of the existing compression component, so as to ensure that the engine is It can work stably under the condition of temperature distortion.

[0022] The method for adjusting the adjustable guide vanes of the aero-engine compression components proposed in the present application is as follows:

[0023] The main compression components of the engine, such as fans or comp...

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Abstract

The present application provides a method for adjusting an adjustable guide vane of a compression part of an aero-engine to cope with temperature distortion, comprising: arranging at least two temperature sensors at different positions of the engine inlet or the inlet of the compression part in the circumferential direction, for measuring the inlet of the engine or the inlet of the compression part temperature; determine the difference between the highest value and the lowest value of the temperature sensor, if the difference between the highest value and the lowest value is greater than a predetermined value, the value of the temperature sensor with the highest value in the temperature sensor is used as the control input, Adjust the adjustable guide vane angle of the compression part; if the difference between the highest value and the lowest value is less than a predetermined value, the average value of the temperature sensor is used as the control input to adjust the adjustable guide vane of the compression part angle. The method of the present application can improve the engine's ability to resist temperature distortion with less sacrifice in performance, and can also achieve stability expansion only when temperature distortion is encountered, which is beneficial to improve the performance of other flight positions within the entire envelope except for temperature scenarios.

Description

technical field [0001] The application belongs to the technical field of aero-engines, and in particular relates to a method for adjusting guide vanes of aero-engine compression components to cope 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 intake 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 time sequence, that is, Spatial inhomogeneities and temporal steps. After the temperature distortion superimposes the pressure distortion of the intake port itself, it will have an important impact on the performance and stability of the engine, and even lead to engine surge in severe cases, affecting flight safety. [0003] There are many scenarios that produce temperature distortion, such as: when the aircraft is flying in...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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