Seal for a thrust reverser of a turbojet engine nacelle

Patent metadata

Field	Value
Publication number	US-9670874-B2
Application number	US-201615093798-A
Country	US
Kind code	B2
Filing date	Apr 8, 2016
Priority date	Oct 11, 2013
Publication date	Jun 6, 2017
Grant date	Jun 6, 2017

Abstract

The present disclosure relates to a seal for an aircraft turbojet engine nacelle thrust reverser, the seal having body having a cross section with respect to a longitudinal axis of the seal that is substantially circular, and a base which is intended to be mounted in a seal support. The seal is notable in that the base of said seal has apertures spaced from each other.

First claim

What is claimed is:

1. A seal for a thrust reverser of an aircraft turbojet engine nacelle, said seal comprising a body having a cross-section of which with respect to a longitudinal axis (L) of the seal is substantially circular and a base mounted in a seal support affixed on a surface of the thrust reverser, wherein the base includes an end portion with a rectangular cross section and an opposite end portion having an inverted D-shaped cross section, the end portion with the rectangular cross section including apertures spaced from each other, the apertures formed normal to the surface, the seal support comprising holding tabs which have an L-shape, wherein each holding tab extends through one of the apertures.

2. The seal according to claim 1 , wherein the apertures are substantially aligned with each other along the longitudinal axis (L) of the seal.

3. The seal according to claim 1 , wherein the apertures are evenly spaced.

4. The seal according to claim 1 , wherein the apertures have a substantially rectangular shape.

5. The seal according to claim 1 , wherein the apertures extend through the base of the seal along a substantially vertical axis (V) of said seal.

6. The seal according to claim 1 , wherein the holding tabs of the seal support are substantially aligned with each other along a longitudinal axis (L) of said seal support.

7. The seal according to claim 1 , wherein the holding tabs of the seal support are positioned at a longitudinal end portion of the seal support.

8. The seal according to claim 1 , wherein the holding tabs of the seal support are evenly spaced.

9. The seal according to claim 1 , wherein the holding tabs of the seal support have a substantially “L”-shaped cross-section with respect to the longitudinal axis (L) of the seal support.

10. The seal according to claim 1 , wherein the seal support comprises one single curved longitudinal end portion.

11. The seal according to claim 1 , wherein a longitudinal length of the holding tabs of the seal support is substantially equal to a longitudinal length of the apertures of the seal.

12. The seal according to claim 1 , wherein a transverse length of the holding tabs of the seal support is substantially equal to a transverse length of an end portion of the base of the seal.

13. The thrust reverser for an aircraft turbojet engine nacelle, comprising vanes and at least one cowl alternately movable between a position according to which the cowl covers said vanes, and a position according to which the cowl uncovers said vanes, said cowl being equipped with a seal according to claim 1 , in which the seal cooperates with a deflecting edge of the thrust reverser when said cowl covers said vanes.

Assignees

• Aircelle Sa

Inventors

• Provost Fabrice

Classifications

• F05D2240/55

  Seals · CPC title

• F02K1/566 Primary

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

• F02K1/72

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

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F02K1/805

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