Nacelle for an aircraft turbojet engine comprising a secondary nozzle section with rotary doors

Patent metadata

Field	Value
Publication number	US-10100780-B2
Application number	US-201615364623-A
Country	US
Kind code	B2
Filing date	Nov 30, 2016
Priority date	May 30, 2014
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

The present disclosure relates to a turbojet engine nacelle having an external cowling with an internal wall defining, with an internal fixed structure, an annular flow channel for a secondary airflow and an exhaust nozzle for said secondary airflow. The nozzle includes at least one opening, at least one continuous downstream end portion, downstream of said opening, and at least one door moving between a closed position and an open position allowing the passage of a part of said airflow through said opening. The nacelle is notable in that it includes a shaped device for activation of the door, during their activation from a closed position to an open position of the door, to drive the door in a combined movement that is translational in the direction running upstream from the nacelle and rotary towards the exterior of the nacelle.

First claim

What is claimed is:

1. A nacelle for an aircraft turbojet engine comprising: an inner fixed structure defining at least partially a fairing of the aircraft turbojet engine;
an outer cowling comprising an upstream section and a downstream section, said downstream section comprising an outer wall and an inner wall defining, with the inner fixed structure, an annular flow channel of an air flow, said downstream section comprising an ejection nozzle of said air flow, said ejection nozzle comprising:
at least one opening in the downstream section of the outer cowling;
at least one continuous downstream end portion, downstream of said at least one opening;
at least one door alternately movable, upon activation of an actuating device, between a dosed position sealing said at least one opening and providing aerodynamic continuity of the nacelle, and an open position allowing passage of at least one portion of the air flow through said at least one opening, from the annular flow channel towards an outside of the nacelle,
wherein the at least one door comprises a door inner wall and a door outer wall, wherein the door inner wall and the door outer wall are immovable relative to each other, and wherein when the door is in the closed position, the door inner wall provides inner aerodynamic continuity of the nacelle and the door outer wall provides outer aerodynamic continuity of the nacelle,
wherein the actuating device, upon activation of said actuating device from the closed position to the open position of the at least one door, is operable to drive said at least one door into a simultaneous combined movement in translation upstream of the nacelle and in rotation outwardly of the nacelle, wherein the entire at least one door translates upstream during the simultaneous combined movement, and in that the actuating device comprises:
at least one actuator comprising an upstream body secured to a fixed portion of the nacelle, and a rod having one end directly connected to an upstream wall of said at least one door; and
at least one connecting rod having an end connected to the outer cowling of the nacelle and another end of which is connected to the at least one door of the ejection nozzle,
wherein when the at least one door is translated, the at least one connecting rod is also translated and causes simultaneous rotation of the at least one door.

2. The nacelle according to claim 1 , wherein the at least one door comprises a trailing edge shaped to at least partially cover the at least one continuous downstream end portion of the ejection nozzle.

3. The nacelle according to claim 2 , wherein the trailing edge of the at least one door has a curved profile.

4. The nacelle according to claim 2 , wherein the trailing edge of the at least one door has a tapered profile such that a tangent to a lower surface of the at least one door is parallel to a wall of the continuous downstream end portion positioned opposite said trailing edge.

5. The nacelle according to claim 1 further comprising a sealing device disposed between the at least one door and the outer cowling and arranged to oppose a flow of air on a perimeter of the at least one door and through the at least one opening when the at least one door is in the closed position.

6. The nacelle according to claim 1 , wherein at least one of the at least one door and the outer cowling further comprises at least one fixed or movable lateral flap proximate the at least one opening.

7. The nacelle according to claim 1 , wherein the upstream section of the outer cowling and the continuous downstream end portion of the ejection nozzle are made as a single piece.

8. The nacelle according to claim 1 further comprising a thrust reverser device.

9. The nacelle according to claim 1 , wherein the at least one door is acoustically treated.

Assignees

• Safran Nacelles

Inventors

• Tissot Sarah
• Bouteiller Xavier
• Kerbler Olivier
• Gonidec Patrick

Classifications

• F02K1/09 Primary

  by axially moving an external member, e.g. a shroud (F02K1/12 takes precedence) · CPC title

• F02K1/1261

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

• F05D2250/42

  with two degrees of freedom · CPC title

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F02K3/06

  with front fan · CPC title