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Thrust reverser

A thrust reverser and actuator technology, applied in the direction of machines/engines, high-efficiency propulsion technology, jet propulsion devices, etc., can solve the problems of complicated engine entry, long and difficult operation, etc., to simplify the interface and eliminate backlash , the effect of good aerodynamic performance

Active Publication Date: 2013-06-12
AIRCELLE +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0019] Regardless of the mode of maintenance access chosen, such operations are lengthy and difficult, and involve the installation of separate elements in areas subject to significant structural stress
[0020] Engine entry is also tedious

Method used

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Examples

Experimental program
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Embodiment Construction

[0041] refer to figure 1 , the aircraft propulsion assembly comprising a nacelle 1 of a turbojet engine 2 suspended under a wing (not shown) using islands 3 designed as interfaces and rods or racks (not shown).

[0042] The nacelle 1 is generally subdivided into an upstream air intake section, a middle section surrounding the fan (not shown) of the turbojet engine 2 and its casing, and a downstream section housing thrust reversal equipment 20, and optionally a terminal nozzle section .

[0043] The nacelle is shown with a so-called "O" shaped downstream section.

[0044] Such as image 3 and Figure 4 It is shown that the thrust reverser device 20 can take the form of a cowl 21 which can be translated longitudinally in the downstream direction of the nacelle 1 so as to be able to open an opening in the external downstream structure of the nacelle 1 and expose the grille Vanes 22 capable of redirecting part of the secondary flow of air generated by the turbojet engine towar...

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PUM

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Abstract

The invention relates to a thrust reverser for the nacelle of a turboreactor, comprising at least one fixed front frame (25) that can be mounted downstream of a fan casing of said turboreactor and directly or indirectly supports at least one flow deviation means (22), characterised in that at least part of said flow deviation means (22) can be detached from the front frame (25) and moved in translation independently therefrom when a maintenance operation is being carried out on said reverser.

Description

technical field [0001] The invention relates to a thrust reverser for an aircraft engine assembly. Background technique [0002] The aircraft propulsion assembly consists of the nacelle and the turbojet engine and is designed to be suspended from a fixed structure of the aircraft (for example under the wing or at the fuselage) by means of suspension rods attached to the turbine engine or nacelle Down. [0003] A turbojet engine typically comprises a so-called "upstream" section comprising a fan provided with blades, and a so-called "downstream" section accommodating a gas generator. [0004] The blades of the fan are surrounded by the casing making it possible to install the turbojet engine in the nacelle. [0005] The nacelle is generally tubular in shape, comprising an air intake upstream of the turbojet engine, an intermediate section designed to surround the turbojet's fan, and a downstream section housing the thrust reverser and designed to surround the turbojet's gas...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/00F02K1/60F02K1/62F02K1/72F02K1/76
CPCF01D5/005F02K1/605F02K1/625F02K1/72F02K1/766F05D2230/80F05D2240/14Y02T50/60F01D25/24
Inventor 埃尔维·于尔林尼古拉斯·德泽斯特雷奥特·巴尔克贝特朗·德若约
Owner AIRCELLE