Nacelle Of An Aircraft Propulsion Assembly Comprising A Plurality Of Damper Elements Between A Front Section And A Main Section, And Associated Aircraft Propulsion Assembly

Patent metadata

Field	Value
Publication number	US-2020002016-A1
Application number	US-201916440214-A
Country	US
Kind code	A1
Filing date	Jun 13, 2019
Priority date	Jun 28, 2018
Publication date	Jan 2, 2020
Grant date	—

Abstract

A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.

First claim

1 . A nacelle of an aircraft propulsion assembly, comprising:
a front section and a main section, said front section having a front end forming an air intake in the nacelle and a rear end comprising an annular stiffening frame around a rotary axis, said stiffening frame comprising an outer peripheral edge, connected to an outer panel of the nacelle, and an inner peripheral edge, said front section further comprising a connection part connecting said inner peripheral edge of the stiffening frame to an inner structure of the nacelle and a junction flange connected to said inner peripheral edge of the stiffening frame and to an engine flange of the main section, wherein the junction flange comprises a plurality of deformable damper elements distributed along said inner peripheral edge of the stiffening frame.

2 . The nacelle according to claim 1 , wherein at least one of the connections between the junction flange and the stiffening frame and between the junction flange and the engine flange comprises a spacer adapted to deform under the effect of mechanical stresses between said engine flange and said stiffening frame.

3 . The nacelle according to claim 1 , wherein each damper element is formed by a bridge of material having a hollow closed section.

4 . The nacelle according to claim 3 , wherein said hollow closed section forms a cavity, into which an elastomer element is inserted.

5 . The nacelle according to claim 4 , wherein said elastomer element comprises at least one recess of material.

6 . The nacelle according to claim 4 , wherein said elastomer element extends between at least two surfaces of said damper element.

7 . The nacelle according to claim 1 , wherein at least one damper element comprises a bridge of material and an elastomer element, said bridge of material comprises a hollow open section and said elastomer element lines the inner walls of said damper element.

8 . The nacelle according to claim 1 , wherein at least one damper element comprises an armature and an elastomer element, said armature comprising a substantially S-shaped section, wherein said armature is fully or partly included in said elastomer element.

9 . The nacelle according to claim 1 , wherein each damper element has a section of substantially oval, for example, elliptical, or circular shape.

10 . The nacelle according to claim 1 , comprising common connections between the stiffening frame, the connection part and the damper elements of the junction flange.

11 . The nacelle according to claim 1 , wherein the connections between the stiffening frame and the junction flange and between the junction flange and the engine flange each comprise at least one screw and nut assembly, and wherein each damper element of the junction flange comprises a first side and a second side that respectively comprise supports adapted to receive and retain the nuts of said screw and nut assemblies.

12 . The nacelle according to claim 1 , wherein said junction flange comprises a sealing flange formed by a ring having a substantially U-shaped section, and wherein one branch of the “U” is connected to said stiffening frame and other branch of the “U” is connected to said engine flange.

13 . The nacelle according to claim 12 , wherein the sealing flange, the damper element and the stiffening frame, on the one hand, and the sealing flange, the damper element and the engine flange, on the other hand, are connected together by common connections such as screw and nut systems.

14 . The nacelle according to claim 1 , wherein the connections between the stiffening frame and the junction flange, on the one hand, and between the junction flange and the engine flange, on the other hand, are circumferentially offset from each other so as not to be facing each other.

15 . An aircraft propulsion assembly comprising a nacelle, said nacelle being a nacelle according to claim 1 .

Assignees

• Airbus Operations Sas

Inventors

• Breton Clément
• Sentier Julien
• Vinches Frédéric
• Porte Alain
• Brochard Wolfgang

Classifications

• B64D29/06 Primary

  Attaching of nacelles, fairings or cowlings · CPC title

• B64D29/00 Primary

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D33/02 Primary

  of combustion air intakes · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title