Aircraft provided with an exhaust duct coupled to a stabilization system

Patent metadata

Field	Value
Publication number	US-12466570-B2
Application number	US-202318380289-A
Country	US
Kind code	B2
Filing date	Oct 16, 2023
Priority date	Nov 9, 2022
Publication date	Nov 11, 2025
Grant date	Nov 11, 2025

Abstract

An aircraft provided with at least one exhaust duct for discharging gases from an engine. The exhaust duct is partly accommodated in an internal housing of the aircraft, the housing being separated from an external environment situated outside the aircraft by at least one cowl that is able to move in relation to a load-bearing structure of the aircraft. The exhaust duct comprises an exhaust segment passing through a passage of the cowl without touching the cowl. A space separates the exhaust segment from the cowl. The aircraft comprises at least one stabilization system coupled to the exhaust duct, the stabilization system comprising a stiffening ring secured to the exhaust duct and at least one fastening connecting the exhaust duct to the cowl.

First claim

What is claimed is:

1 . An aircraft provided with at least one exhaust duct for discharging gases from an engine, the exhaust duct being partly accommodated in an internal housing of the aircraft, the housing being separated from an external environment situated outside the aircraft by at least one cowl, the cowl being able to move in relation to a load-bearing structure of the aircraft, the exhaust duct comprising an exhaust segment passing through a passage of the cowl without touching the cowl, a space separating the exhaust segment from the cowl,
wherein the aircraft comprises at least one stabilization system coupled to the exhaust duct, the stabilization system comprising a stiffening ring secured to the exhaust duct and at least one fastening connecting the exhaust duct to the cowl.

2 . The aircraft according to claim 1 ,
wherein the stiffening ring surrounds the exhaust duct.

3 . The aircraft according to claim 1 ,
wherein the stiffening ring extends over an angle of less than 360 degrees around a geometric axis.

4 . The aircraft according to claim 1 ,
wherein the stiffening ring is arranged around the exhaust segment.

5 . The aircraft according to claim 1 ,
wherein the stiffening ring is arranged at least partially in the external environment.

6 . The aircraft according to claim 1 ,
wherein the stiffening ring comprises an L-shaped, T-shaped, C-shaped or omega-shaped profile.

7 . The aircraft according to claim 1 ,
wherein the stiffening ring is attached to the exhaust duct by removable stiffening fasteners.

8 . The aircraft according to claim 1 ,
wherein the at least one fastening comprises a first support secured to the exhaust duct and a second support secured to the cowl, the at least one fastening comprising a connecting fastener attaching the first support to the second support.

9 . The aircraft according to claim 1 ,
wherein the at least one fastening is arranged at least partially in the housing.

10 . The aircraft according to claim 1 ,
wherein the at least one fastening is accessible via the space separating the exhaust segment from the cowl.

11 . The aircraft according to claim 1 ,
wherein the at least one fastening(s) is adjacent to the stiffening ring.

12 . The aircraft according to claim 1 ,
wherein the at least one fastening is fastened to the stiffening ring.

13 . The aircraft according to claim 1 ,
wherein the at least one fastening comprises several fastenings arranged around the exhaust duct.

14 . An aircraft having an exhaust duct for discharging gases from an engine, the exhaust duct partly accommodated in an internal housing of the aircraft, the housing separated from an external environment situated outside the aircraft by a cowl, the cowl moveable in relation to a load-bearing structure of the aircraft, the exhaust duct comprising an exhaust segment passing through a passage of the cowl without touching the cowl such that a space separates the exhaust segment from the cowl,
wherein the aircraft comprises a ring secured to the exhaust duct and a fastener connecting the exhaust duct to the cowl.

15 . The aircraft according to claim 14 ,
wherein the ring is a stiffening ring that surrounds the exhaust duct.

16 . The aircraft according to claim 14 ,
wherein the ring extends over an angle of less than 360 degrees around a geometric axis.

17 . The aircraft according to claim 14 ,
wherein the ring is arranged around the exhaust segment.

18 . The aircraft according to claim 14 ,
wherein the ring is arranged at least partially in the external environment.

19 . The aircraft according to claim 14 ,
wherein the ring comprises an L-shaped, T-shaped, C-shaped or omega-shaped profile.

20 . The aircraft according to claim 14 ,
wherein the fastener comprises a first support secured to the exhaust duct and a second support secured to the cowl, the fastener attaching the first support to the second support, and wherein the fastener is arranged at least partially in the housing.

Assignees

• Airbus Helicopters

Inventors

• Legras Guillaume
• Morente Franck
• Pinto Philippe
• Felmy Kevin

Classifications

• B64D29/08

  Inspection panels for power plants · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F05D2220/329

  in helicopters · CPC title

• F02K1/80

  Couplings or connections · CPC title