Turbojet engine nacelle having a variable nozzle

Patent metadata

Field	Value
Publication number	US-9587583-B2
Application number	US-201414173484-A
Country	US
Kind code	B2
Filing date	Feb 5, 2014
Priority date	Aug 5, 2011
Publication date	Mar 7, 2017
Grant date	Mar 7, 2017

Abstract

A turbojet engine nacelle has a thrust reverser device and an actuating system for said thrust reverser device, and the thrust reverser device includes a moving cowl mounted translatably alternating between a closed position and an open position, and a jet nozzle section for gases that extends the moving cowl. In particular, the jet nozzle section includes a nozzle flap mounted movable between a closed position and an open position in which the nozzle flap opens a leakage passage toward the outside of the nozzle section. The actuating system has an actuator shared with the moving cowl and the nozzle flap to activate the translational movement of the moving cowl and to pivot the nozzle flap between three following positions: an idle position, an open position of the nozzle flap and an open position of the moving cowl.

First claim

What is claimed is:

1. A turbojet engine nacelle, comprising a thrust reverser device and an actuating system for said thrust reverser device, said thrust reverser device comprising:
at least one moving cowl mounted translatably in a direction substantially parallel to a longitudinal axis of the nacelle alternating between a closed position, in which said moving cowl provides the aerodynamic continuity of the nacelle, and an open position, in which said moving cowl opens a passage in the nacelle for a deflected flow, the moving cowl comprising multiple reverser flaps; and
at least one jet nozzle section for gases that extends said moving cowl and includes at least one nozzle flap mounted movable between a closed position and at least one open position in which said nozzle flap opens a leakage passage toward the outside of the nozzle section,
wherein the nozzle flap is mounted pivoting on the moving cowl, and the actuating system comprises actuating means shared with the moving cowl and the nozzle flap and activates the translational movement of the moving cowl and the pivoting of the nozzle flap between three following positions:
a first position, called idle position, in which the moving cowl is in its closing position and the nozzle flap is in its closed position;
a second position, called open position of the nozzle flap, in which the moving cowl is in its closing position and the jet nozzle is in its open position; and
a third position, called open position of the moving cowl, in which the moving cowl is in its open position and the nozzle flap is in its closed position.

2. The turbojet engine nacelle according to claim 1 , wherein the actuating means activate the translation of the moving cowl from its open position toward its closing position, and next activate the pivoting of the nozzle flap from its closed position toward its open position while keeping the moving cowl in its closed position.

3. The turbojet engine nacelle according to claim 1 or 2 , wherein the actuating means activate the pivoting of the nozzle flap from its open position to its closed position, and next activate the translational movement of the moving cowl from its closed position toward its open position or keeping the nozzle flap in its closed position.

4. The turbojet engine nacelle according to claim 1 , wherein the thrust reverser device comprises a front fixed structure supporting at least one flow deflecting means housed inside the moving cowl in its open position, the actuating means being mounted on said first fixed structure.

5. The turbojet engine nacelle according claim 1 , wherein the nozzle flap is pivotably mounted on an inner wall of the moving cowl.

6. The turbojet engine nacelle according to claim 1 , wherein the nozzle flap switches from its closed position to its open position by pivoting toward the outside of the nozzle section.

7. The turbojet engine nacelle according to claim 1 , wherein the actuating means comprise a linear actuator provided with a hollow body inside which a translatable rod is housed, said translatable rod crossing through the moving cowl and having a free end fixed on the nozzle flap.

8. The turbojet engine nacelle according to claim 7 , wherein the translatable rod of the linear actuator is movable between:
the first position, called the idle position, when the translatable rod controls the moving cowl in its closing position and the jet nozzle section in its closed position;
the second position, called the open position of the nozzle flap, in which the translatable rod is retracted inside the hollow body relative to the first position, said translatable rod keeping the moving cowl in its closing position and controlling the pivoting of the nozzle flap toward its open position by going from the first to the second position; and
the third position, called the open position of the moving cowl, in which the translatable rod is deployed outside the hollow body relative to the first position, said translatable rod controlling the translational movement of the moving cowl toward its open position and keeping the nozzle flap in its closed position by going from the first to the third position.

9. The turbojet engine nacelle according to claim 7 , wherein the hollow body is fixed on the front fixed structure.

Assignees

• Aircelle Sa

Inventors

• Caruel Pierre
• Gonidec Patrick
• Boileau Patrick

Classifications

• F02K1/72

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• F02K1/12

  by means of pivoted flaps · CPC title

• F02K1/30

  for varying effective area of jet pipe or nozzle · CPC title

• F02K1/06 Primary

  Varying effective area of jet pipe or nozzle (by using fluid jets to influence the jet flow F02K1/30) · CPC title

• F02K1/625

  the aft end of the engine cowling being movable to uncover openings for the reversed flow · CPC title