Self-protection control method of aero-engine in unwarmed state

An aero-engine, protection and control technology, applied in the direction of engine starting, engine components, engine ignition, etc., can solve problems such as surge stall, low work efficiency, and increased engine vibration value

Active Publication Date: 2021-03-02
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

When the engine is not warmed up, due to problems such as the mismatch of the engine rotor-stator gap, low aerodynamic stability, and low work efficiency, the drastic state change when the accelerator is pushed up quickly may lead to increased engine vibration and certain Probability of surge stall...

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  • Self-protection control method of aero-engine in unwarmed state
  • Self-protection control method of aero-engine in unwarmed state

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Embodiment Construction

[0023] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...

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Abstract

The invention belongs to the field of aircraft engine design, and relates to a self-protection control method of an aero-engine in an unwarmed state. The method comprises the following steps that an engine starting mode and an engine state are acquired; if the engine starting mode is cold-state starting and the engine state is a slow running state or a state below the slow running state, a controlinstruction of a throttle lever PLA is received to start the engine; and if the engine starting mode is cold-state starting and the engine state is a state above the slow running state, a control instruction of a built-in throttle lever PLA is received to start the engine, wherein the control instruction of the built-in throttle lever PLA changes along with the trend of the control instruction ofthe throttle lever PLA, and the change rate is controlled within a set value. After the entering condition of warm-up starting is met, the built-in throttle lever PLA is used for replacing a mechanical throttle PLA to control the engine, and the problem of engine surge caused by quick push-up of a throttle is effectively avoided.

Description

technical field [0001] The application belongs to the field of aircraft engine design, and in particular relates to a self-protection control method for an aero-engine when it is not warmed up. Background technique [0002] When the military small bypass ratio engine is left overnight and then restarted, the engine is in a cold working mode. At this time, the engine needs to be warmed up by pushing up the accelerator to achieve a better engine working condition. When the engine is not warmed up, due to problems such as the mismatch of the engine rotor-stator gap, low aerodynamic stability, and low work efficiency, the drastic state change when the accelerator is pushed up quickly may lead to increased engine vibration and certain Probability of a surge stall, accelerated engine performance attenuation. In the unwarmed state, it is important to intuitively control the engine state change. The current third-generation domestic aircraft and the An-31f engine have not been opti...

Claims

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Application Information

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IPC IPC(8): F02C7/26F02C9/50B64D31/02
CPCF02C7/26F02C9/50B64D31/02
Inventor 赵肃施磊万东凯康忱王阳李泳凡阎巍
Owner AECC SHENYANG ENGINE RES INST
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