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Bypass turbojet engine and aircraft including the same

A turbojet and engine technology, applied in the field of aircraft, can solve problems such as vibration of gooseneck assemblies

Active Publication Date: 2022-07-19
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] While these hinges with gooseneck fittings allow for good air flow, the gooseneck fittings hinged at their two ends may vibrate when the movable cowl is in the closed position

Method used

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  • Bypass turbojet engine and aircraft including the same
  • Bypass turbojet engine and aircraft including the same
  • Bypass turbojet engine and aircraft including the same

Examples

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Embodiment Construction

[0026] In the following description, the terms referring to position refer to the normal position of the forward traveling aircraft, that is, as figure 1 depicted.

[0027] figure 1 An aircraft 100 is shown that includes a fuselage 102 having wings 104 on each side. At least one bypass turbojet 110 is secured under each wing 104 by means of pylons 106 .

[0028] Throughout the following description, by convention, the direction X corresponds to the longitudinal direction of the bypass turbojet 110 , which direction is parallel to the longitudinal axis of the bypass turbojet 110 . Furthermore, the direction Y corresponds to the direction oriented laterally with respect to the bypass turbojet 110, and the direction Z corresponds to the vertical direction or height, the three directions X, Y, and Z being mutually orthogonal.

[0029] figure 2 A bypass turbojet 110 is shown having a composition similar to that of a prior art bypass turbojet and includes a central core 202 tha...

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PUM

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Abstract

The invention relates to a bypass turbojet and an aircraft, the bypass turbojet comprising: a fixed structure (50); a central core; and a fairing, the fairing comprising a fixed part and a movable fairing (206b) , the movable fairing is mounted with the ability to rotate between closed and open positions on the stationary structure via a hinge (208) with a gooseneck fitting. At least one hinge (208) with a gooseneck fitting includes a gooseneck fitting (209b) having one end hingedly mounted on the movable fairing (206b) and in a hinged manner One end mounted on the stationary structure (50), the bypass turbojet includes an anti-vibration device (350) intended to abut the gooseneck fitting (209b) when the movable fairing is in the closed position )put pressure on. The presence of the anti-vibration device prevents the gooseneck assembly from vibrating when the movable fairing is in the closed position.

Description

technical field [0001] The invention relates to a bypass turbojet for an aircraft, the bypass turbojet comprising a fairing mounted with rotation relative to a stationary structure by means of a hinge with a gooseneck fitting Ability. The invention also relates to an aircraft comprising at least one such bypass turbojet. Background technique [0002] Aircraft conventionally comprise at least one wing under which a pylon is fixed, to which the bypass turbojet is attached. [0003] A prior art bypass turbojet includes a central core that constitutes an engine with combustion chambers, a fan in front of the central core, and inner and outer fairings that constitute a secondary (bypass) flow The inner wall of the path and extending around the central core, the outer fairing constitutes the outer wall of the secondary (bypass) flow path and extends around the inner fairing. [0004] In order to allow maintenance on the bypass turbojet, the inner and outer fairings each compris...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D27/26B64D27/18B64D27/40
CPCB64D27/18B64D27/404B64D27/40B64D29/06B64D29/08E05D5/06E05D2005/067E05Y2900/502B64C1/14E05D7/1066
Inventor 让·热利奥阿德利纳·苏利耶
Owner AIRBUS OPERATIONS (SAS)