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Fluid discharge vibration damping strips for acoustic protection of aircraft turbomachine fan casing

一种声学保护、振动阻尼的技术，应用在用于弹性流体的泵送装置的部件、飞机上动力装置、飞机零件等方向，能够解决不能完全令人满意等问题

Active Publication Date: 2014-08-20
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

So this workaround is not entirely satisfactory

Method used

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  • Fluid discharge vibration damping strips for acoustic protection of aircraft turbomachine fan casing
  • Fluid discharge vibration damping strips for acoustic protection of aircraft turbomachine fan casing
  • Fluid discharge vibration damping strips for acoustic protection of aircraft turbomachine fan casing

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Embodiment Construction

[0036] First reference figure 1 , Which represents the fan cover 1, which is defined as the main part of the front part of the aircraft turbojet aircraft engine. Preferably, the aircraft turbojet aircraft engine is of a dual-flow dual-rotor type.

[0037] The cover assumes a conventional ferrule shape with a longitudinal axis 2 that coincides with the longitudinal axis of the turbojet engine assembly.

[0038] At its upstream end, the inner surface 1a of the cover 1a is equipped with a plurality of acoustic protection devices 4, figure 1 Only one of them is shown in.

[0039] The device 4 includes an acoustic protection plate 6 that forms a ferrule sector part centered on the same central axis as the longitudinal axis 4. When all the protection devices are installed on the cover, its plates 6 which are continuous with each other in the circumferential direction together form an internal acoustic protection ring.

[0040] Preferably, the plate 6 is assembled on the cover by screws, and...

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PUM

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Abstract

The invention relates to an acoustic protection device (4) for an aircraft turbomachine fan casing, comprising an acoustic protection panel (6) forming a shell ring sector centred on a central axis (2), the device also comprising one or more vibration damping strips (10) pressed firmly on one side against the exterior surface (6a) of the panel (6) and on the other side against an interior surface of the casing, each damping strip (10) having two opposite edge faces (14) each having an upstream end and a downstream end which are spaced apart in the direction of the central axis (2). According to the invention, at least one of the two opposite edge faces (14) of at least one of the damping strips (10) is shaped in such a way that the liquid present on this edge face can flow under gravity toward one / or the other of its upstream and downstream ends.

Description

Technical field [0001] The invention relates to the installation of acoustic protection inside the fan cover of an aircraft turbine. More specifically, the present invention is related to the vibration damping strip provided between the fan cover and the acoustic panel. [0002] The invention can be applied to any type of aircraft equipped with a fan cover, especially to turbojet aircraft engines. Background technique [0003] On current turbojet aircraft engines, acoustic protection panels are generally mounted on the inner surface of the fan cover and around the axis of the engine. The assembly is usually performed by fixing the plate to the cover with screws. [0004] However, some fixing screws of the acoustic panel have been identified as having a risk of failure. In the event of a failure, the screw head released in the jet can cause high damage to the fan blade after being sucked in. Among the main reasons for the identification, there is strong vibration stress caused by ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/66F02C7/045B64D33/02
CPCB64D33/02B64D2033/0206F02C7/045F01D25/32F04D29/668F04D19/002F04D29/663F04D29/66
Inventor 纪尧姆·罗非朱利安·特雷
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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