Nacelle

Patent metadata

Field	Value
Publication number	US-10968864-B2
Application number	US-201916553939-A
Country	US
Kind code	B2
Filing date	Aug 28, 2019
Priority date	Jan 27, 2012
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

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 comprising a cascade and an outlet cowling, the cascade being radially inward relative to the outlet cowling, the outlet cowling comprising:
a translating sleeve panel comprising an aft end and a first lateral side;
an outer fixed structure, the outer fixed structure comprising a first lateral side;
an outer track on the first lateral side of the outer fixed structure;
a forward thrust configuration where the aft end of the translating sleeve panel is in a first position relative to the outer fixed structure; and
a reverse thrust configuration where the aft end of the translating sleeve panel is in a second position relative to the outer fixed structure, wherein the second position is longitudinally aft of the first position, wherein the translating sleeve panel slides along the outer track in moving between the forward thrust configuration and the reverse thrust configuration, and wherein the translating sleeve panel is configured to expose the cascade in response to translating aftward to the reverse thrust configuration, thereby allowing air to be redirected in a forward direction via the cascade in the reverse thrust configuration,
wherein the first lateral side of the translating sleeve panel is adjacent to the first lateral side of the outer fixed structure,
wherein the translating sleeve panel is configured to translate longitudinally aftward relative to the outer fixed structure via the outer track in moving from the forward thrust configuration to the reverse thrust configuration.

2. The nacelle of claim 1 , further comprising an inner translating sleeve panel that is located radially inward from the translating sleeve panel and forms a cavity between the translating sleeve panel and the inner translating sleeve panel.

3. The nacelle of claim 2 , further comprising a groove in the outer fixed structure that forms the outer track and is configured to receive a slider that is attached to the translating sleeve panel.

4. The nacelle of claim 3 , wherein the outer fixed structure extends into the cavity between the translating sleeve panel and the inner translating sleeve panel.

5. The nacelle of claim 3 , wherein the translating sleeve panel further comprises an outer transverse side and an inner transverse side, wherein the outer transverse side is radially outward of the inner transverse side, and wherein the slider of the translating sleeve panel is attached to the inner transverse side of the translating sleeve panel and disposed adjacent to the first lateral side of the outer fixed structure.

6. The nacelle of claim 1 , wherein the outer track extends a length of the outer fixed structure in a longitudinal direction.

7. The nacelle of claim 1 , wherein the outer fixed structure further comprises a hinge access panel adjacent to the outer fixed structure, wherein the second lateral side of the outer fixed structure is closer to a nacelle pylon than the first lateral side of the outer fixed structure in an installed configuration for the outlet cowling.

8. The nacelle of claim 5 , wherein the cascade is radially inward of the outer transverse side of the translating sleeve panel in the cavity between the translating sleeve panel and the inner translating sleeve panel, wherein the translating sleeve panel and the inner translating sleeve panel are configured to expose the cascade in response to translating aftward, thereby allowing air to be redirected in the forward direction via the cascade.

9. A nacelle comprising:
a cascade;
an inlet cowling;
an outlet cowling separated from the inlet cowling by a transverse split line, the cascade being radially inward relative to the outlet cowling, the outlet cowling including:
a translating sleeve panel comprising an aft end and a first lateral side; and
an outer fixed structure comprising a track and a first lateral side adjacent to the first lateral side of the translating sleeve panel;

a forward thrust configuration where the aft end of the translating sleeve panel is in a first position relative to the outer fixed structure; and
a reverse thrust configuration where the aft end of the translating sleeve panel is in a second position relative to the outer fixed structure, wherein the second position is longitudinally aft of the first position, wherein the outer fixed structure remains in the same position for each of the forward thrust configuration and the reverse thrust configuration, and wherein the translating sleeve panel slides along the track in moving between the forward thrust configuration and the reverse thrust configuration;
wherein the translating sleeve panel is configured to expose the cascade in response to translating longitudinally aftward relative to the outer fixed structure via the track in moving from the forward thrust configuration to the reverse thrust configuration, thereby allowing air to be redirected in a forward direction via the cascade.

10. The nacelle of claim 9 , wherein the outlet cowling further comprises an inner translating sleeve panel that is located radially inward from the translating sleeve panel and forms a cavity between the translating sleeve panel and the inner translating sleeve panel.

11. The nacelle of claim 9 , further comprising a groove in the outer fixed structure that forms the track and is configured to receive a slider that is attached to the translating sleeve panel.

12. The nacelle of claim 10 , wherein the outer fixed structure extends into the cavity between the translating sleeve panel and the inner translating sleeve panel.

13. The nacelle of claim 11 , wherein the translating sleeve panel further comprises an outer transverse side and an inner transverse side, wherein the outer transverse side is radially outward of the inner transverse side, and wherein the slider of the translating sleeve panel is attached to the inner transverse side of the translating sleeve panel and disposed adjacent to the first lateral side of the outer fixed structure.

14. The nacelle of claim 9 , further comprising a pylon, wherein the track is on the first lateral side of the outer fixed structure, wherein the track extends a length of the outer fixed structure in a longitudinal direction, and wherein the outer fixed structure is located between the pylon and the translating sleeve.

15. The nacelle of claim 9 , wherein the outer fixed structure further comprises a hinge access panel adjacent to the outer fixed structure.

16. The nacelle of claim 13 , wherein the cascade is radially inward of the outer transverse side of the translating sleeve panel in the cavity between the translating sleeve panel and the inner translating sleeve panel, wherein the translating sleeve panel and the inner translating sleeve panel are configured to expose the cascade in response to translating aftward in moving from the forward thrust configuration to the reverse thrust configuration, thereby allowing air to be redirected in the forward direction via the cascade.

17. A method of reversing thrust of an engine fitted with a nacelle on an aircraft, the nacelle comprising an outlet cowling, wherein the outlet cowling comprises a translating sleeve panel, an inner translating sleeve panel, and an outer fixed structure, the method comprising:
changing the outlet cowling from a forward thrust configuration to a reverse thrust configuration, comprising moving the translating sleeve panel and the inner translating sleeve panel longitudinally from a first position corresponding with the forward thrust configuration to a second position corresponding with the reverse thrust confi

Assignees

• Rohr Inc

Inventors

• Aten Michael Ray
• Crawford Sara

Classifications

• 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

• F02K1/82 Primary

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

• B64D33/04

  of exhaust outlets or jet pipes · CPC title

• Y02T70/50

  Measures to reduce greenhouse gas emissions related to the propulsion system · CPC title

• B64D29/02

  associated with wings · CPC title