Nacelle

Patent metadata

Field	Value
Publication number	US-9784216-B2
Application number	US-201514939638-A
Country	US
Kind code	B2
Filing date	Nov 12, 2015
Priority date	Jan 27, 2012
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

A nacelle is configured to be coupled to an underside of a wing and forms a clearance space between the nacelle and a leading edge slat of the wing. A portion of an outlet cowling moves longitudinally aft when a reverse thrust configuration is activated and the leading edge slat is deployed toward the nacelle. The outlet cowling also includes another portion located adjacent to the leading edge slat that does not move when the reverse thrust configuration is activated and thus maintains its clearance space from the leading edge slat.

First claim

What is claimed is:

1. An outlet cowling of a nacelle, the nacelle configured to be coupled to an underside of a wing, the wing comprising a leading edge slat, the outlet cowling having a circumference comprising a top portion configured to be located proximate the wing when the nacelle is coupled to the underside of the wing, the outlet cowling comprising:
a sliding portion forming a first portion of the circumference, the sliding portion configured to move longitudinally between a forward thrust position and a reverse thrust position; and
at least one stationary portion adjacent to the sliding portion and forming a second portion of the circumference, the at least one stationary portion configured to be located aft of a transverse split line between the outlet cowling and an inlet cowling, the transverse split line extending between the inlet cowling and a forward portion of the at least one stationary portion, the transverse split line separating the inlet cowling from the stationary portion, the at least one stationary portion remaining in a stationary position when the sliding portion moves between the forward thrust position and the reverse thrust position,
wherein the leading edge slat is configured to move between a stowed position and a deployed position, and
wherein the at least one stationary portion occupies a space between the outer sliding portion and the wing which prevents interference between the sliding portion and the leading edge slat upon movement of the sliding portion.

2. The outlet cowling of claim 1 further comprising an inner translating sleeve disposed radially inward of the sliding portion and the at least one stationary portion, wherein the sliding portion is configured to move aft longitudinally in conjunction with the inner translating sleeve.

3. The outlet cowling of claim 1 further comprising at least one track, the at least one track forming at least a portion of a mating engagement between the sliding portion and the at least one stationary portion.

4. The outlet cowling of claim 3 , wherein the at least one track is disposed in the sliding portion.

5. The outlet cowling of claim 4 , wherein the at least one track extends for the longitudinal length of the sliding portion.

6. The outlet cowling of claim 3 , wherein the at least one track is disposed in the at least one stationary portion.

7. The outlet cowling of claim 4 , wherein the at least one track extends for the longitudinal length of the at least one stationary portion.

8. The outlet cowling of claim 1 further comprising a tongue and a groove, one of the groove and tongue being disposed in the at least one stationary portion and the other one of the groove and tongue being disposed in the sliding portion.

9. A nacelle configured to be coupled to an underside of a wing, the wing comprising a leading edge slat configured to extend toward the nacelle when in a deployed configuration, the nacelle comprising:
an inlet cowling; and
an outlet cowling separated from the inlet cowling by a transverse split line, the outlet cowling including:
an outer translating sleeve configured to move aft in a longitudinal direction; and
an outer fixed structure located aft of the transverse split line, a forward portion of the outer fixed structure forming a portion of the transverse split line, the transverse split line separating the inlet cowling from the outer fixed structure, the outer fixed structure configured to be located between the outer translating sleeve and the wing to prevent interference between the other translating sleeve and the leading edge slat upon movement of the outer translating sleeve.

10. The nacelle of claim 9 , wherein the outlet cowling further comprises an inner translating sleeve configured to move with the outer translating sleeve aft in the longitudinal direction.

11. The nacelle of claim 9 further comprising an upper track beam, wherein the outer fixed structure is coupled to the upper track beam.

12. The nacelle of claim 9 further comprising a cascade located radially inward of the outer translating sleeve, wherein the cascade is not disposed underneath the outer fixed structure.

13. The nacelle of claim 9 further comprising a plurality of blocker doors, a portion of at least one blocker door being located radially inward of the outer fixed structure.

14. The nacelle of claim 9 further comprising an access panel located outboard of the pylon, wherein the outer fixed structure is located between the access panel and the outer translating sleeve.

15. The nacelle of claim 9 , wherein the outer fixed structure is located outboard of the pylon.

16. The nacelle of claim 9 , wherein the outer fixed structure is located inboard of the pylon.

17. The nacelle of claim 9 , wherein the outer fixed structure is located outboard of a pylon coupling the nacelle to the underside of the wing, and further comprising a second outer fixed structure located inboard of the pylon, a clearance distance between the leading edge slat in the deployed configuration and the second outer fixed structure remaining substantially constant when the outer translating sleeve moves aft in the longitudinal direction.

18. A method of reversing thrust of an engine fitted with a nacelle on an aircraft, the nacelle comprising an outlet cowling including an outer translating sleeve and an outer fixed structure located adjacent to an inboard lateral side of the outer translating sleeve, the method comprising:
moving the outer translating sleeve longitudinally from a first position to a second position aft of the first position without moving the outer fixed structure, the outer fixed structure being located aft of a transverse split line between the outlet cowling and an inlet cowling, the transverse split line extending between the inlet cowling and a forward portion of the outer fixed structure, the transverse split line separating the inlet cowling from the outer fixed structure,
wherein the nacelle is configured to be coupled to an underside of a wing, the wing comprising a leading edge slat configured to extend toward the nacelle when in a deployed configuration,
wherein the outer fixed structure is configured to be located between the outer translating sleeve and the wing to prevent interference between the outer translating sleeve and the leading edge slat upon movement of the outer translating sleeve.

19. The method of claim 18 further comprising moving an inner translating sleeve from a first position to a second position aft of the first position, wherein at least a portion of the inner translating sleeve is disposed radially inward of the outer translating sleeve.

20. The method of claim 19 further comprising moving a plurality of blocker doors from a first position relative to the inner translating sleeve to a second position relative to the inner translating sleeve, the second position being different than the first position.

Assignees

• Rohr Inc

Inventors

• Aten Michael Ray
• Crawford Sara

Classifications

• B64D29/02

  associated with wings · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• F02K1/82 Primary

  Jet pipe walls, e.g. liners · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F02K1/566

  by blocking the rearward discharge by means of a translatable member · CPC title