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Engine assembly for aircraft

An engine and aircraft technology, applied in power plant types, jet power units, etc., to solve problems such as engine bending, engine efficiency reduction, friction, etc.

Inactive Publication Date: 2008-05-14
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] In another case, the applicable functional clearance is pre-set so as to achieve hardly any contact caused by the longitudinal curvature, and the engine efficiency is thus greatly reduced
[0013] On the other hand, it has been observed that, for example, after a sudden strong wind in the vertical or horizontal direction, other engine bending phenomena occur, which tend to cause friction between the rotating blades of the compressor and turbine and the central casing of the engine

Method used

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  • Engine assembly for aircraft
  • Engine assembly for aircraft
  • Engine assembly for aircraft

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Embodiment Construction

[0033] Referring to Figure 1 , there can be seen an aircraft engine assembly 1 according to a first preferred embodiment of the invention, intended to be fixed under an aircraft wing (not shown).

[0034] On the whole, the engine assembly 1 comprises a turbojet engine 2, a pylon 4, and a plurality of engine connectors 6a, 6b, 8, 9 for ensuring that the turbojet engine 2 is fixed on the bottom of the pylon 4 (the connector 6b is shown in Fig. 1 is blocked by the connector 6a). It is worth noting that the assembly 1 is surrounded by a nacelle (not shown) and that the pylon 4 comprises a further series of connections (not shown) ensuring that the assembly 1 is suspended under the wing of the aircraft.

[0035] In all the ensuing elaborations, the direction parallel to the longitudinal axis 5 of the turbojet 2 will be called X, the direction of transverse orientation relative to the same turbojet 2 will be called Y, and the vertical or height direction As Z, the three directions ...

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Abstract

The invention relates to an aircraft engine unit (1) comprising a jet engine (2), a suspension pylon (4) and a plurality of engine fasteners. According to said invention, the plurality of fasteners comprises first (6a) and second (6b) front fasteners which are fixed to the fan case of the engine and positioned symmetrically with respect to a plane (P) defined by a longitudinal axis (5) of the jet engine and a vertical direction (Z) thereof, wherein the first and second fasteners are constructed in such a way that they pick up loads produced in the longitudinal direction (X) of the jet engine and in the vertical direction thereof. In addition, the plurality of fasteners also comprises a rear engine fastener (9) constructed in such a way that it picks up loads produced in the vertical direction.

Description

technical field [0001] The invention relates primarily to an aircraft engine assembly, of the type comprising a turbojet, a pylon, and engine connections interposed between the pylon and the turbojet. Background technique [0002] As is known, the pylon of an engine assembly is used to form the connection interface between the turbojet engine and the wing of the aircraft equipped with this assembly. The pylon is capable of transmitting the forces generated by the associated engine to the structure of the aircraft and also allows the passage of fuel, electrical, hydraulic and air between the engine and the aircraft. [0003] In order to ensure the transmission of force, the hanger ( ) includes, for example, rigid structures of the "box girder" type, ie rigid structures constituted by the assembly of spars and side panels interconnected by means of transverse ribs. [0004] The mounting system is interposed between the engine and the rigid structure of the pylon, and the sy...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/18B64D27/40
CPCB64D27/18
Inventor 利昂内尔·迪奥雄让-米歇尔·塞陶特奥利维耶·特卢
Owner AIRBUS OPERATIONS (SAS)