Air intake for aircraft nacelle, and propulsion assembly including such air intake

Patent metadata

Field	Value
Publication number	US-8985506-B2
Application number	US-86490109-A
Country	US
Kind code	B2
Filing date	Jan 21, 2009
Priority date	Jan 29, 2008
Publication date	Mar 24, 2015
Grant date	Mar 24, 2015

Abstract

The invention relates to an air intake for an aircraft nacelle that includes a shroud that can be mounted on the fan casing of a turbojet engine. The shroud is sized so as to define a circumferential gap relative to the casing. Punctual linking means between the shroud and the casing are discretely distributed at the periphery of the shroud.

First claim

The invention claimed is:

1. An air intake for aircraft nacelle comprising a shroud being mounted on a fan casing of a turbojet engine, said shroud being dimensioned to define a circumferential gap relative to said casing, the shroud comprising discrete support beams distributed equidistantly around a circumference of the shroud, the support beams directly connecting said shroud to said casing without any intermediate connection part between said shroud and said casing, wherein the air intake does not include any structural member to connect said shroud to said casing circumferentially between the support beams, thereby allowing for radial movements of the shroud relative to the casing between the support beams.

2. The air intake according to claim 1 , further comprises lugs mounted articulated on said support beams and being fastened on said casing.

3. The air intake according to claim 2 , in which said lugs are adapted to be mounted on a flange integrated to said fan casing.

4. The assembly according to claim 3 , in which the upstream edge of said casing includes a flange on which said lugs are fastened.

5. The air intake according to claim 2 , in which said lugs are adapted to be mounted directly on an outer face of said casing.

6. The air intake according to claim 1 , wherein said shroud is an acoustic shroud.

7. The air intake according to claim 1 , in which said shroud is adapted to extend in part under an upstream edge of said casing.

8. The assembly according claim 1 , in which an inner face of said casing includes a step defining the gap between said shroud and said casing.

9. The assembly according to claim 8 , in which said step has a ramp.

10. A propulsion assembly for aircraft comprising an assembly according to claim 1 .

Assignees

• Vauchel Guy Bernard
• Valleroy Laurent Georges
• Beilliard Stéphane
• Bravin Fabien
• Aircelle Sa

Inventors

• Vauchel Guy Bernard
• Valleroy Laurent Georges
• Beilliard Stéphane
• Bravin Fabien

Classifications

• F02C7/045

  having provisions for noise suppression · CPC title

• B64D2033/0286

  for turbofan engines · CPC title

• B64D33/02 Primary

  of combustion air intakes · CPC title

• F01D21/00

  Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for · CPC title

• B64D2033/0206

  comprising noise reduction means, e.g. acoustic liners · CPC title