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An aircraft engine assembly comprising at least two rear engine attachments axially shifted from each other

A technology for engines and aircraft, applied in the field of engine components, can solve the problems of size increase, large total width of rear engine attachments, aerodynamic disturbance of overall engine performance, etc., and achieve the effect of reducing mass and total mass

Active Publication Date: 2017-08-04
AIRBUS OPERATIONS SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The three connecting rods 102 are laterally spaced, which results in a relatively large overall width of the rear engine attachment
Such oversizing increases the size of the rear attachment or rear mounted fairing (RMF), which may be in the form of a local enlargement around the two lateral ends of the rear engine attachment, causing a negative impact on the overall performance of the engine Aerodynamic disturbances with adverse effects

Method used

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  • An aircraft engine assembly comprising at least two rear engine attachments axially shifted from each other
  • An aircraft engine assembly comprising at least two rear engine attachments axially shifted from each other
  • An aircraft engine assembly comprising at least two rear engine attachments axially shifted from each other

Examples

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Embodiment Construction

[0055] figure 2 Shown is an aircraft 200 comprising two wing system units 2 ( figure 2 Only visible is the fuselage 3 of one wing system unit 2) each supporting an engine assembly 5 according to the invention. The engine assembly 5 comprises a twin-flow catamaran engine 10 , such as a turbojet engine, and a mounting pylon 4 for the engine 10 .

[0056] image 3 One of the engine assemblies 5 is shown in more detail. Shown are wing system units 2 , turbojet engines 10 and mounting pylons 4 . Furthermore, mounting means 8 for the pylon 4 are arranged on the wing system unit 2 and mounting means 7a, 7b, 7c for the turbojet engine 10 are arranged on the pylon. These mounting means 7a, 7b, 7c, the pylon 4 and the turbojet 10 form the engine assembly 5 according to the invention.

[0057] The mounting means 8 positioned at the junction between the pylon 4 and the wing system unit 2 are formed in a conventional manner. Therefore, the mounting device 8 will not be described in...

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Abstract

In order to reduce the width of the attachment means between the rear portion of an aircraft engine and its attachment pylon, the invention provides an engine assembly, the attachment means of which include an assembly of rear engine attachments (7a) comprising: - a first connecting rod (7a1) laid out in a longitudinal and median vertical plane; - a second connecting rod (7a2) substantially laid out tangentially to the inter-turbine case (46); and - a rear engine attachment (7a3) for transversely spreading the loads, axially shifted rearwards relatively to the first and second connecting rods (7a1, 7a2), and comprising a shear pin (64) oriented along a vertical direction (Z) of the engine assembly.

Description

technical field [0001] The invention relates to the field of engine assemblies of aircraft comprising a pylon for mounting the engine on a structural part of the aircraft, preferably under a wing of said aircraft. [0002] The invention relates more particularly to engine assemblies in which the rear engine attachment connects the main structural member of the pylon to the inter-turbine casing of the engine. [0003] The invention is preferably applied to commercial aircraft. Background technique [0004] On existing aircraft, engines such as twin-flow catamaran turbojets are suspended below the wing system by complex mounting systems known as Engine Mounting Structures (EMS) or mounting pylons. Commonly used mounting hangers have rigid structural members known as primary structural members. Such a primary structural member usually forms a box, that is, it is formed by assembling upper and lower stringers secured by reinforcing transverse ribs positioned within the box. c...

Claims

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Application Information

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IPC IPC(8): B64D27/26
CPCB64D27/404B64D27/40F02C7/20B64D27/406B64D27/402B64D27/18F02K1/08
Inventor 奥利维耶·波蒂斯沃尔夫冈·布罗沙尔
Owner AIRBUS OPERATIONS SAS