Load shedding device for fan blade out (FBO) event of aero-engine

A technology of aero-engine and fan blades, which is applied in the direction of engine components, engine control, gas turbine devices, etc., and can solve problems such as engine shedding, broken blades breaking through the cabin, engine installation joints, and damage to key components of bearings, etc.

Active Publication Date: 2020-02-18
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The FBO event will generate a huge unbalanced load, which may cause damage to key components such as engine mounting joints and bearings, and cause catastrophic accidents such as engine falling off and broken leaves breaking through the engine room.

Method used

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  • Load shedding device for fan blade out (FBO) event of aero-engine
  • Load shedding device for fan blade out (FBO) event of aero-engine
  • Load shedding device for fan blade out (FBO) event of aero-engine

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Embodiment Construction

[0018] A variety of different implementations or examples for implementing the described subject technical solutions are disclosed below. In order to simplify the disclosure, the following describes the specific examples of each component and arrangement, of course, these are only examples, not limiting the protection scope of the present invention. For example, the description that the first feature described later in the description is formed on or above the second feature may include an embodiment in which the first and second features are formed through direct contact, and may also include an embodiment in which the first and second features are formed between the first and second features. Embodiments of additional features such that there may be no direct relationship between the first and second features. Additionally, reference numerals and / or letters may be repeated in different instances in these disclosures. This repetition is for brevity and clarity and does not i...

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PUM

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Abstract

The invention provides a load shedding device and method for a fan blade out (FBO) event of an aero-engine. According to the load shedding device and method, when a fusing part of a low-pressure rotoris out of operation under the FBO load effect, the critical rotating speed of the low-pressure rotor can still be adjusted bidirectionally. The load shedding device comprises the fusing part, a fan shaft, two or more sensors and a controller, and the fusing part is arranged on a bearing seat or bearing conical wall of a first bearing; the fan shaft comprises an intelligent telescopic structure; the two or more sensors are used for monitoring dynamic response of the first bearing and a second bearing; and the controller is correlated with the sensors and the intelligent telescopic structure, wherein the sensors detect abnormal dynamic responses of the first bearing and the second bearing and transmit the detected dynamic responses to the controller, the controller sends signals to the intelligent telescopic structure, thus the intelligent telescopic structure can extend and retract in a predetermined range, and the length of the fan shaft is changed.

Description

technical field [0001] The invention relates to an aero-engine, in particular to a load reduction device for an aero-engine fan blade shedding event. Background technique [0002] According to the requirements of airworthiness regulations (FAR33.74, FAR33.94), commercial aircraft engines must ensure that the occurrence of FBO events (fan blade off events) will not lead to catastrophic consequences. The FBO event will generate a huge unbalanced load, which may cause damage to key components such as engine mounting joints and bearings, and cause catastrophic accidents such as engine falling off and broken leaves penetrating the nacelle. Immediately following an FBO event, the damaged engine should be shut down, allowing the engine to slowly decelerate from a higher operating speed to windmill speed, and remain in the windmill phase for a period of time (sometimes as much as 180 minutes) until landing conditions are met Slow down and land safely. [0003] In order to ensure t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C9/00
CPCF02C9/00F05D2270/09F01D21/14F01D25/16F02C7/00
Inventor 赵芝梅郑李鹏宋会英王少辉唐振南
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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