Nacelle for an aircraft turbojet engine with an extended front lip

Patent metadata

Field	Value
Publication number	US-9969499-B2
Application number	US-201514885422-A
Country	US
Kind code	B2
Filing date	Oct 16, 2015
Priority date	Apr 19, 2013
Publication date	May 15, 2018
Grant date	May 15, 2018

Abstract

A nacelle for an aircraft turbojet engine includes: a substantially cylindrical internal envelope, a substantially cylindrical external envelope, a downstream partition wall and an upstream partition wall secured to the cylindrical internal envelope and a front lip disposed forward of the upstream partition wall. The cylindrical internal envelope includes an upstream portion including an acoustic shroud connected, by an attachment flange, to a downstream portion including a fan casing. In particular, the front lip is extended and disposed over the upstream partition wall by presenting a downstream edge between the upstream and downstream partition walls in order to be secured to a homologous edge of the cylindrical external envelope so as to arrange a maintenance access to the attachment flange.

First claim

What is claimed is:

1. A nacelle for an aircraft turbojet engine including a substantially cylindrical internal envelope, a substantially cylindrical external envelope, a downstream partition wall and an upstream partition wall secured to said cylindrical internal envelope and a front lip disposed forward of the upstream partition wall, the cylindrical internal envelope comprising an upstream portion including an acoustic shroud connected, by an attachment flange, to a downstream portion including a fan casing,
wherein the attachment flange is disposed between the upstream partition wall and the downstream partition wall, and no intermediate wall is disposed between the upstream partition wall and the downstream partition wall, and
wherein the front lip is extended and disposed over the upstream partition wall includes a downstream edge disposed between the upstream and downstream partition walls and secured to a homologous edge of the cylindrical external envelope so as to arrange a maintenance access to said attachment flange.

2. The nacelle according to claim 1 , wherein the downstream partition wall is disposed on the fan casing at a limit of a rest area of a thrust reverser, and the cylindrical external envelope extends beyond the thrust reverser on said downstream partition wall.

3. The nacelle according to claim 1 , wherein the cylindrical external envelope is fastened by fastening means also to an edge of the downstream partition wall.

4. The nacelle according to claim 1 , wherein the fastening of homologous edges of the extended front lip and the cylindrical external envelope comprises at least one annular plate which carries means of fastening to the downstream edge of the extended front lip and to the homologous edge of the cylindrical external envelope.

5. The nacelle according to claim 4 , wherein said at least one annular plate is integral with an internal face of the downstream edge of the extended front lip.

6. The nacelle according to claim 1 , wherein the extended front lip and/or the cylindrical external envelope are made of at least two angular sectors.

7. The nacelle according to claim 6 , wherein at least one angular sector of the cylindrical external envelope is provided with removable means of fastening to the extended front lip, removable means of fastening to the downstream partition wall and removable means of fastening to an adjacent angular sectors of the cylindrical external envelope.

8. The nacelle according to claim 1 , wherein the extended front lip and/or the cylindrical external envelope is made of metal.

9. The nacelle according to claim 8 , wherein an internal face of the cylindrical external envelope and/or the extended front lip comprises annular reinforcements.

10. The nacelle according to claim 8 , wherein the extended front lip and/or the cylindrical external envelope is made of aluminum.

11. The nacelle according to claim 1 , wherein the extended front lip and/or the cylindrical external envelope is made of a composite material.

12. The nacelle according to claim 1 , wherein the nacelle comprises at least one additional partition wall angular sector, secured to an internal envelope of an inlet section of the nacelle and disposed between the upstream partition wall and the downstream partition wall.

Assignees

• Aircelle Sa

Inventors

• Caruel Pierre

Classifications

• B64D33/02 Primary

  of combustion air intakes · CPC title

• B64D2033/0206

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

• F05D2220/327

  to drive shrouded, high solidity propeller · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• B64D2033/0273

  for jet engines · CPC title