Method for acquiring thrust limiting rules of big and small accelerator of aircraft engine

A technology for an aircraft engine and an acquisition method, applied in the aviation field, can solve problems such as aggravating engine service life loss, reducing engine stability margin, engine stall or surge, etc., and achieving the effects of improving working strength and service life and improving stability.

Active Publication Date: 2018-11-27
AECC SHENYANG ENGINE RES INST
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Problems solved by technology

In order to take into account the performance of the throttle, the fuel supply during the acceleration process is greatly increased. This adjustment will cause the following problems: the higher acceleration fuel will increase the loss of engine life; the engine stability margin will be

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  • Method for acquiring thrust limiting rules of big and small accelerator of aircraft engine
  • Method for acquiring thrust limiting rules of big and small accelerator of aircraft engine
  • Method for acquiring thrust limiting rules of big and small accelerator of aircraft engine

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Embodiment Construction

[0028] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. 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 invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses a method for acquiring thrust limiting rules of big and small accelerators of an aircraft engine. The method comprises the following steps: calculating a state deviation valueof the engine, and determining whether the engine is in an acceleration state according to the state deviation value; if the engine is in the acceleration state, acquiring a low-pressure rotor conversion rotational speed control rule curve of the engine when parameters of the aircraft meet the first preset condition; and determining a low-pressure rotor conversion rotational speed corresponding toa first preset time in the low-pressure rotor conversion rotational speed control rule curve, and calculating a fuel oil flow curve of the engine according to the low-pressure rotor conversion rotational speed. By utilizing the control method implemented in the invention, the supply amounts of the fuel oil flow during the actions of the big and small accelerators of the engine can be independently controlled, and the requirement of the thrust change rate is realized.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a method for acquiring the law of limiting throttle thrust of an aircraft engine. Background technique [0002] When the aircraft performs a landing and go-around, the engine needs to provide a large thrust instantly. This requires the engine thrust to respond quickly over time, and this response characteristic is the engine throttle characteristic. The thrust response characteristics of large throttle refers to the thrust response characteristics of the engine from the approach and landing state (thrust is within a certain range) when the throttle lever is quickly pushed up to the intermediate state according to the requirements of the carrier-based aircraft. The large throttle thrust characteristics of the engine can make the aircraft Acceleration gain is obtained for a short time after throttle stick action. The small throttle thrust response characteristic refers to the f...

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Application Information

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IPC IPC(8): F02C9/26F02C9/44
Inventor 郭海红韩文俊邴连喜崔金辉邢洋
Owner AECC SHENYANG ENGINE RES INST
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