Nacelle

Patent metadata

Field	Value
Publication number	US-8931736-B2
Application number	US-201414246352-A
Country	US
Kind code	B2
Filing date	Apr 7, 2014
Priority date	Jan 27, 2012
Publication date	Jan 13, 2015
Grant date	Jan 13, 2015

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. A nacelle configured to be coupled to an underside of a wing via a pylon, the wing comprising a leading edge slat configured to extend toward the nacelle when in a deployed configuration, the nacelle comprising:
a cowling including:
a first outer translating sleeve half configured to move aft in a longitudinal direction;
a second outer translating sleeve half configured to move aft in the longitudinal direction,

wherein a bottom of a translating sleeve comprises the first outer translating sleeve half and a top of the translating sleeve comprises the second outer translating sleeve half; and
an outer fixed structure having a clearance distance to the leading edge slat which remains substantially constant in response to the leading edge slat being in the deployed configuration, wherein a shape defined by the combination of the second outer translating sleeve half and the outer fixed structure is substantially symmetrical to the shape defined by the first outer translating sleeve half.

2. The nacelle of claim 1 , wherein the cowling further comprises an inner translating sleeve configured to move with the second outer translating sleeve half aft in the longitudinal direction.

3. The nacelle of claim 1 , further comprising an upper track beam, wherein the outer fixed structure is coupled to the upper track beam.

4. The nacelle of claim 1 , further comprising a cascade located radially inward of the second outer translating sleeve half, wherein the cascade is not disposed underneath the outer fixed structure.

5. The nacelle of claim 1 , further comprising a plurality of blocker doors, a portion of at least one blocker door being located radially inward of the outer fixed structure.

6. The nacelle of claim 1 , further comprising an access panel located outboard of the pylon, wherein the outer fixed structure is located between the access panel and the second outer translating sleeve half.

7. The nacelle of claim 1 , wherein the outer fixed structure is located outboard of the pylon.

8. The nacelle of claim 1 , wherein the outer fixed structure is located inboard of the pylon.

9. The nacelle of claim 1 , 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 a second outer translating sleeve half moves aft in the longitudinal direction.

10. The nacelle of claim 1 , wherein the first outer translating sleeve half and the second outer translating sleeve half are asymmetrical.

11. A method of reversing thrust of an engine fitted with a nacelle on an aircraft, the nacelle comprising a cowling including a first outer translating sleeve half, a second outer translating sleeve half, and an outer fixed structure located adjacent to an inboard lateral side of the second outer translating sleeve half, wherein a shape defined by the combination of the second outer translating sleeve half and the outer fixed structure is substantially symmetrical to the shape defined by the first outer translating sleeve half, wherein a bottom of a translating sleeve comprises the first outer translating sleeve half and a top of the translating sleeve comprises the second outer translating sleeve half, the method comprising:
maintaining the first outer translating sleeve half, the second outer translating sleeve half and the outer fixed structure in a first position; and
moving the first outer translating sleeve half and the second outer translating sleeve half longitudinally from the first position to a second position aft of the first position while maintaining the outer fixed structure fixed in the first position.

12. The method of claim 11 , 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 first outer translating sleeve half and the second outer translating sleeve half.

13. The method of claim 12 , 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

• F02K1/54

  Nozzles having means for reversing jet thrust (reversing jet thrust using fluid jets F02K1/32) · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F02K1/566 Primary

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

• 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