Integrated thrust reverser device and aircraft engine nacelle equipped therewith

Patent metadata

Field	Value
Publication number	US-9816462-B2
Application number	US-201615017931-A
Country	US
Kind code	B2
Filing date	Feb 8, 2016
Priority date	Aug 7, 2013
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

The present disclosure provides a thrust reverser device that is integrated in an aircraft nacelle. Blocking flaps are stored inside a mobile cowl disposed in a downstream section of the nacelle, under deflection cascade assemblies during direct-jet operation of the nacelle. Various devices are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: the mobile cowl moves in translation towards the downstream end of the nacelle; and each flap is then deployed in the main air flow path.

First claim

What is claimed is:

1. A thrust reverser device for an aircraft engine nacelle comprising:
a cowl alternately movable between a deployed position wherein the cowl opens a passage within the nacelle, said deployed position being adapted to allow a reverse jet operation of said nacelle, and a stowed position wherein the cowl closes the passage, said stowed position being adapted to allow a direct jet operation of the nacelle;
a set of cascade vanes of a secondary air flow flowing in a flow path of the nacelle, said set of cascade vane fixed upstream of said cowl;
flaps for blocking the secondary air flow, alternately movable between:
a folded position wherein the flaps are stored, at least for a stowed position of said cowl, within said cowl and under said set of cascade vanes, and
an open position wherein the flaps block at least partially the secondary air flow flowing in said flow path,

a controller for executing switching from the direct jet operation to the reverse jet operation, the operation comprising two stages:
1. translation of the cowl downstream of the nacelle to the deployed position of said cowl, said flaps being in the folded position; and
2. opening of the flaps from said folded position to said open position,

wherein the flaps include an upstream edge mounted on a slide secured to said set of cascade vanes and a downstream edge mounted on a lever articulated relative to said set of cascade vanes, wherein the upstream edge of the flaps is driven downstream by the slide in the deployed position.

2. The thrust reverse device according to claim 1 , wherein the flaps have a trapezoidal shape, and a reduction of an aeramatch is achieved by at least one of:
gaps between lateral edges of the flaps are occupied by movable triangular inter-flaps, wherein the gaps are gradually removed when the flaps go down within a direct air flow path, and reintroduced when the flaps return under the set of cascade vanes:
the gaps between the lateral edges of the flaps are occupied by triangular inter-flaps secured to the set of cascade vanes, the lateral edges of the flaps having spoilers in thickness for diverting intercepted jets; and
the lateral edges of adjacent flaps have determined thickness profiles to provide overlapping of the lateral edges of the flaps when the flaps are deployed in the direct air flow path.

3. An aircraft engine nacelle including a thrust reverser device according to claim 1 .

4. The thrust reverser device according to claim 1 , wherein the flaps remain in the folded position until the cowl has moved to the deployed position.

5. The thrust reverser device according to claim 1 , wherein the flaps are not pivoted when the cowl is moved from the stowed position to the deployed position.

6. The thrust reverser device according claim 1 , wherein the controller for executing the switching from the direct jet operation to the reverse jet operation performed in two stages include cowl mobilization cylinders secured to an upstream section of the nacelle through a front frame of the nacelle in order to mobilize the cowl, a bearing secured to the cowl and being fixed to an end of a movable pin of each of said cowl mobilization cylinders, the set of cascade vanes being secured to the front frame, the front frame of the nacelle being disposed at a downstream end of the nacelle.

7. The thrust reverser device according to claim 6 , further comprising two cowl mobilization cylinders disposed on either side of a 12 o'clock position and a cowl mobilization cylinder disposed substantially at a 6 o'clock position.

8. The thrust reverser device according to claim 1 , wherein the controller for executing the switching from the direct jet operation to the reverse jet operation performed in two stages includes blocking flap cylinders secured to the set of cascade vanes, each having a worm gear on which an articulation device is secured to an upstream edge of a flap and being constrained to move in order to handle the flap between a folded position under the set of cascade vanes and the open position through a direct air flow path so that air flow from the direct air flow path is directed through the set of cascade vanes.

9. The thrust reverser device according to claim 8 , wherein the front frame of the nacelle and the cowl are configured to be locked during maintenance operations, so that the front frame, the set of cascade vanes, the flaps, the blocking flap cylinders, and the cowl are operated as an assembly by means of at least one cowl mobilization cylinder for handling the cowl in maintenance.

10. The thrust reverser device according to claim 1 , wherein the controller for executing the switching from the direct jet operation to the reverse jet operation carried out in two stages includes cowl mobilization cylinders and blocking flap mobilization cylinders integrated into a plurality of combined cylinders including an inner pin for driving the cowl and a threaded outer tube for causing movement of a nut secured to the upstream edge of a flap.

11. The thrust reverser device according to the claim 10 , wherein the plurality of combined cylinder includes a first drive shaft coupled to the inner pin by a movement conversion mechanism, and at least a second drive shaft coupled to the threaded outer tube by another conversion mechanism.

12. The thrust reverser device according to claim 11 , wherein the cowl includes a flange disposed beyond a volume occupied by the plurality of combined cylinders, the set of cascade vanes, the flaps and levers of the flaps when the cowl is closed and in that the flange carries bearings on which are secured ends of movable pins of the plurality of combined cylinders in order to mobilize the cowl.

13. The thrust reverser device according to claim 10 , wherein the plurality of combined cylinders are secured to a front flange of the cowl.

Assignees

• Aircelle Sa

Inventors

• Guerin Philipe
• Kerbler Olivier
• Rami Jean-Paul

Classifications

• F02K1/76

  Control or regulation of thrust reversers · CPC title

• F02K1/62

  by blocking the rearward discharge by means of flaps · CPC title

• F02K3/06

  with front fan · CPC title

• F02K1/763

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

• F02K1/70

  using thrust reverser flaps or doors mounted on the fan housing · CPC title