Exhaust cone with flexible fitting

Patent metadata

Field	Value
Publication number	US-11519361-B2
Application number	US-201917267361-A
Country	US
Kind code	B2
Filing date	Aug 9, 2019
Priority date	Aug 10, 2018
Publication date	Dec 6, 2022
Grant date	Dec 6, 2022

Abstract

An assembly for an aircraft turbojet engine is described. The assembly includes a central gas-exhaust element and a connecting flange interposed between, upstream, a metallic outlet of a turbojet engine and, downstream, the central element. The connecting flange consists of an annular part and flexible lugs having axially: a first end where the lug is connected to the annular part, and a second free end, projecting radially outwards from the first end and towards which the lug is fixed with the central element.

First claim

The invention claimed is:

1. An assembly for an aircraft turbojet engine, the assembly comprising:
a central element for exhausting gas, which is annular about an axis and is configured to have gas exhausted by the turbojet engine around it, from upstream to downstream; and
a connecting flange interposed between, upstream, a metallic outlet of the turbojet engine and, downstream, the central element, to join the metallic outlet and the central element together,
wherein the connecting flange comprises an annular portion and flexible lugs arranged circumferentially around the axis, each flexible lug extending parallel with the axis and having axially:
a first end where the lug is connected to said annular portion, and
a second free end towards which said lug is fixed with the central element, the second free end being located axially upstream of the first end,

wherein the central element has a peripheral wall having an upstream end portion, the upstream end portion being fixed with said respective second free ends of said flexible lugs, and
wherein the upstream end portion of the central element extends parallel to said axis, towards said respective second ends of said flexible lugs, so as to be joined together by screws passing therethrough, and
wherein the peripheral wall extends axially upstream, and radially outwardly with respect to said upstream end portion, to cover the upstream end portion except at locations of radial passages for the screws.

2. The assembly according to claim 1 , wherein the flexible lugs extend radially outwardly from the first end or from openings of the connecting flange.

3. The assembly according to claim 2 , wherein one of said plurality of lugs is integrally connected to said annular portion at a part of said annular portion forming a downstream edge of one said opening.

4. The assembly according to claim 1 , wherein the peripheral wall is locally provided with a sound-attenuating structure and the upstream end portion is located upstream of the sound-attenuating structure.

5. The assembly according to claim 4 , wherein the sound-attenuating structure extends axially to the right of said lugs.

6. The assembly according to claim 4 , wherein the sound-attenuating structure is honeycombed.

7. The assembly according to claim 1 , wherein the central element is made of a ceramic matrix composite material and the connecting flange is metallic.

8. An assembly for an aircraft turbojet engine, the assembly comprising:
a central element for exhausting gas, which is annular about an axis and is configured to have gas exhausted by the turbojet engine around it, from upstream to downstream; and
a connecting flange interposed between, upstream, a metallic outlet of the turbojet engine and, downstream, the central element, to join the metallic outlet and the central element together,
wherein the connecting flange comprises an annular portion and, circumferentially around the axis, a plurality of tabs and a plurality of flexible lugs,
wherein the annular portion extends upstream from the plurality of tabs and the plurality of flexible lugs, wherein the tabs of the plurality of tabs are integral upstream with said annular portion,
wherein the flexible lugs of the plurality of flexible lugs respectively extend radially outwardly from the tabs of the plurality of tabs, and
wherein each flexible lug of the plurality of flexible lugs has, axially:
a first end where the flexible lugs are individually connected to respective tabs of the plurality of tabs, and
a second free end towards which said lug is fixed with the central element, the second free end being located axially upstream of the first end,

so that the plurality of flexible lungs are connected to said annular portion by said connections at the respective first ends and by the respective tabs which are integral upstream with said annular portion.

9. An assembly for an aircraft turbojet engine, the assembly comprising:
a central element for exhausting gas, which is annular about an axis and is configured to have gas exhausted by the turbojet engine around it, from upstream to downstream; and
a connecting flange interposed between, upstream, a metallic outlet of a turbojet engine and, downstream, the central element, to join the metallic outlet and the central element together,
wherein the connecting flange comprises an annular portion and, circumferentially around the axis, a plurality of flexible lugs and a plurality of openings passing through the connecting flange,
wherein the annular portion has a first annular portion at a first axial end and a second annular portion at a second axial end located downstream the first annular portion, each opening of the plurality of openings extending between the first annular portion and the second annular portion,
wherein the plurality of flexible lugs each have, axially:
a first end where the flexible lug is connected to said second annular portion, and
a second free end located axially upstream of the first end, and

wherein each lug of the plurality of flexible lugs extends radially outwardly from the first end and from the corresponding opening, so that each opening is radially interposed between the axis and one lug of the plurality of flexible lugs.

Assignees

• Safran Ceram

Inventors

• Conete Eric
• Carrere Benoit

Classifications

• F02K1/827

  Sound absorbing structures or liners · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F02K1/04 Primary

  Mounting of an exhaust cone in the jet pipe · CPC title

• B64D27/16

  of jet type · CPC title