Nacelle for a turbojet engine with a variable nozzle

Patent metadata

Field	Value
Publication number	US-2016115902-A1
Application number	US-201614987302-A
Country	US
Kind code	A1
Filing date	Jan 4, 2016
Priority date	Jul 4, 2013
Publication date	Apr 28, 2016
Grant date	—

Abstract

The present disclosure provides a turbojet engine nacelle having a downstream section including a cowl which is ended with a hinged flap constituting a nozzle. In particular, the hinged flap is hingedly and translatably hinged to the cowl.

First claim

What is claimed is:

1 . A nacelle for a turbojet engine having a downstream section comprising at least one cowling ended by at least one hinged flap forming a nozzle, wherein said at least one hinged flap is pivotally and translatably hinged relative to said at least one cowling.

2 . The nacelle according to claim 1 , wherein said at least one hinged flap is movable in translation between a closed position wherein said at least one hinged flap forms an aerodynamic continuity with said at least one cowling and an open position where said at least one hinged flap is configured to increase an outlet section and open an exhaust space between said at least one hinged flap and said at least one cowling to create a tertiary nozzle.

3 . The nacelle according to claim 1 , wherein the downstream section comprises at least one thrust reverser device.

4 . The nacelle according to claim 1 , wherein said at least one hinged flap comprises at least one rotation index configured to cooperate with a rotation pad corresponding to the nacelle, and wherein when said at least one hinged flap is in a nominal position, said at least one rotation index is received inside a notch of the rotation pad opening onto at least a guide rail associated to the nacelle, said rail configured to receive the rotation index and consequently to guide said at least one hinged flap in translation during a variation of a nozzle section by translation of said at least one hinged flap.

5 . The nacelle according to claim 4 , wherein said at least one hinged flap comprises at least one translation index received inside said at least one guide rail when said at least one hinged flap is in a nominal position, said at least one guide rail further comprising a lateral notch configured to allow a passage of said at least one translation index during a variation of the nozzle section by pivoting said at least one hinged flap.

6 . The nacelle according to claim 4 , wherein the nacelle comprises an additional slide extending along a direction of translation of said at least one hinged flap and ended upstream by a corresponding off-centered notch in the rotation pad, said additional slide and corresponding off-centered notch forming an upstream abutment and a downstream abutment for one end of a drive rod of said at least one hinged flap.

7 . The nacelle according claim 1 , wherein said at least one hinged flap or the nacelle comprises at least one translation guiding slide associated with a complementary tilting slide of the nacelle or of said at least one hinged flap and configured to guide the pivoting of said at least one hinged flap, each of the tilting slide and said at least one translation guiding slide receiving a common translation index.

8 . The nacelle according to claim 7 , wherein the common translation index is carried by a control rod.

9 . The nacelle according to claim 1 , wherein said at least one hinged flap comprises at least one upstream module, movably mounted in translation, and pivotally supporting at least one terminal downstream module.

10 . The nacelle according to claim 9 , wherein said at least one upstream module is common to several downstream modules.

11 . The nacelle according to claim 1 , wherein said at least one hinged flap is equipped with at least one pivoting drive means.

12 . The nacelle according to claim 1 , wherein said at least one hinged flap is configured to perform a thrust vectoring.

13 . The nacelle according to claim 1 , wherein the nozzle is equipped with chevrons.

14 . The nacelle according to claim 1 , wherein said at least one hinged flap is equipped with chevrons.

Assignees

• Aircelle Sa

Inventors

• Kerbler Olivier
• Gilo Olivier
• Gonidec Patrick

Classifications

• F02K1/763

  with actuating systems or actuating devices; Arrangement of actuators for thrust reversers · CPC title

• F02K1/1253

  of one series of flaps hinged at their upstream ends on a fixed structure and of a substantially axially movable external member · CPC title

• F02K1/1207

  of one series of flaps hinged at their upstream ends on a fixed structure (F02K1/1215 - F02K1/1292 take precedence) · CPC title

• F02K1/12

  by means of pivoted flaps · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title