Aeroengine thrust reverser arrangement

Patent metadata

Field	Value
Publication number	US-9784213-B2
Application number	US-201314060044-A
Country	US
Kind code	B2
Filing date	Oct 22, 2013
Priority date	Oct 29, 2012
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

A blocker door for a gas turbine engine thrust reverser having a tray with a base and sidewalls extending about the base to define a volume, the volume being closed by a cover that extends beyond the periphery of the tray. The extension of the cover beyond the periphery provides a sealing feature.

First claim

The invention claimed is:

1. A thrust reverser unit for a gas turbine comprising a cowl having an inner surface, and one or more blocker doors, each blocker door comprising:
a tray with a base and sidewalls extending about the base to define a volume, the volume being closed by a cover that extends beyond the periphery of the tray, wherein an extension of the cover beyond the periphery of the tray provides a flexible sealing feature,
wherein the tray further comprises a flange extending from the sidewalls to which the cover is joined, and wherein the flange extends around the periphery of the tray,
wherein the flexible sealing feature seals against the inner surface of the cowl when the one or more blocker doors are in a stowed position,
wherein the one or more blocker doors comprise a first blocker door and a second blocker door, and
wherein in a deployed position the sealing feature of the first blocker door abuts the sealing feature of the second blocker door.

2. The thrust reverser unit according to claim 1 , wherein the inner surface of the cowl has a land defining a first surface and a depression defining a second surface,
wherein the tray is disposed in the depression of the cowl,
wherein the flexible sealing feature comprises first and second portions, and
wherein the first portion contacts and seals the first surface and the second portion contacts and seals the second surface.

3. The thrust reverser unit according to claim 2 , the cover extending beyond the periphery of the flange.

4. The thrust reverser unit according to claim 2 , wherein the cover comprises a moulded rubber.

5. The thrust reverser unit according to claim 3 , wherein the cover comprises a moulded rubber.

6. The thrust reverser unit according to claim 4 , wherein the cover is perforated.

7. The thrust reverser unit according to claim 4 , wherein the tray contains an acoustic liner.

8. The thrust reverser unit according to claim 7 , wherein the acoustic liner comprises a honeycomb.

9. The thrust reverser unit according to claim 2 , wherein the flexible sealing feature comprises a flat seal, or a “P” seal.

10. The thrust reverser unit according to claim 1 , wherein the inner surface has a land and a depression, the tray being located in the depression and the flexible sealing feature sealing against the land.

11. The thrust reverser unit according to claim 1 , wherein the inner surface has a plurality of depressions, each depression of the plurality of depressions locating a respective tray.

12. The thrust reverser unit according to claim 1 , wherein the inner surface has a land between depressions.

13. The thrust reverser unit according to claim 1 , wherein the cowl is translatable from an axially forward stowed position to an axially rearward deployed position.

14. The thrust reverser unit according to claim 1 , further comprising a linkage connecting one of the blocker doors with the cowl, the linkage configured to translate the cowl from the stowed position to the deployed position to effect employment of the one of the blocker doors from a stowed position against the inner surface of the cowl to a deployed position across a gas turbine bypass duct.

15. The thrust reverser unit according to claim 1 ,
wherein the cover extends beyond the periphery of the flange.

16. The thrust reverser unit according to claim 1 , wherein the cover comprises a moulded rubber.

17. The thrust reverser unit according to claim 16 , wherein the moulded rubber cover has at least one integrally formed “P” seal.

18. The thrust reverser unit according to claim 1 , wherein the cover comprises a facing sheet, wherein the flange provides a surface to which the facing sheet can be joined, and wherein the facing sheet is bonded or secured to the flange.

19. A thrust reverser unit for a gas turbine comprising:
a cowl having an inner surface and one or more blocker doors, the one or more blocker doors comprising:
a tray with a base and sidewalls extending about the base to define a volume;
a cover that extends beyond the periphery of the tray and closes the volume, wherein an extension of the cover beyond the periphery of the tray provides a flexible sealing feature;

wherein the flexible sealing feature seals against the inner surface of the cowl when the one or more blocker doors are in a stowed position,
wherein the one or more blocker doors comprise a first blocker door and a second blocker door, and wherein in a deployed position the sealing feature of the first blocker door abuts the sealing feature of the second blocker door.

20. The thrust reverser unit according to claim 19 ,
wherein the inner surface of the cowl has a land defining a first surface and a depression defining a second surface,
wherein the tray further comprises a flange extending from the sidewalls to which the cover is joined, and wherein the flange extends around the periphery of the tray,
wherein the tray is disposed in the depression of the cowl,
wherein the flexible sealing feature comprises first and second portions, and
wherein the first portion contacts and seals the first surface and the second portion contacts and seals the second surface.

21. The thrust reverser unit according to claim 19 ,
wherein the inner surface of the cowl has a land defining by a first surface and a depression defining a second surface,
the one or more blocker doors further comprising a flange extending from the sidewalls,
wherein the flange extends around the periphery of the tray,
wherein the cover is joined to the flange,
wherein the volume is closed by the cover that is joined to the flange,
wherein the cover extends beyond the periphery of the flange,
wherein the tray is disposed in the depression of the cowl,
wherein the flexible sealing feature comprises first and second portions, and
wherein the first portion contacts and seals the first surface and the second portion contacts and seals the second surface.

22. The thrust reverser unit according to claim 2 , wherein the flexible sealing feature comprises an omega-shaped seal, wherein the first portion of the sealing feature is an elongate portion and the second portion of the sealing feature is a bulbous portion.

23. The thrust reverser unit according to claim 1 , wherein the flexible sealing feature comprises an omega-shaped seal, wherein a first portion of the sealing feature is an elongate portion and a second portion of the sealing feature is a bulbous portion.

24. The thrust reverser unit according to claim 19 , wherein the flexible sealing feature comprises an omega-shaped seal, wherein a first portion of the sealing feature is an elongate portion and a second portion of the sealing feature is a bulbous portion.

25. The thrust reverser unit according to claim 15 , wherein the flexible sealing feature comprises an omega-shaped seal, wherein a first portion of the sealing feature is an elongate portion and a second portion of the sealing feature is a bulbous portion.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Todorovic Predrag

Classifications

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02K1/72 Primary

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

• F02K1/805

  Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps · CPC title

• F02K1/76

  Control or regulation of thrust reversers · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title