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Aeroengine fan blade shedding event load reduction device

A technology of aero-engine and fan blades, which is applied to engine components, engine control, machines/engines, etc. It 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: 2020-09-08
AECC COMML AIRCRAFT ENGINE CO LTD
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  • 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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  • Aeroengine fan blade shedding event load reduction device
  • Aeroengine fan blade shedding event load reduction device
  • Aeroengine fan blade shedding event load reduction device

Examples

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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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Abstract

A load reduction apparatus and method for a fan blade-out (FBO) event of an aero-engine, capable of bidirectionally adjusting the critical speed of a low pressure rotor even after the fuse part of the low pressure rotor fails under the action of an FBO load. The load reduction apparatus comprises a fuse part, a fan shaft, at least two sensors, and a controller. The fuse part is provided on a bearing block or a supporting cone wall of a first bearing. The fan shaft comprises an intelligent extendable structure. The at least two sensors are used for monitoring dynamic responses of the first bearing and a second bearing. The controller is disposed in association with the sensors and the intelligent extendable structure separately. 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 a signal to the intelligent extendable structure so that said structure extends or retracts within a predetermined range, so as to change the length of the fan shaft.

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 Patents(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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