Thrust reverser with displaceable trailing edge body

Patent metadata

Field	Value
Publication number	US-11053887-B2
Application number	US-201816025431-A
Country	US
Kind code	B2
Filing date	Jul 2, 2018
Priority date	Jul 2, 2018
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

An assembly is provided for an aircraft propulsion system. This assembly includes a target-type thrust reverser and a tubular trailing edge body. The target-type thrust reverser includes a plurality of thrust reverser doors. Each of the thrust reverser doors is configured to pivot between a stowed position to a deployed position. The tubular trailing edge body is configured to at least partially form a gas path nozzle for the aircraft propulsion system. The tubular trailing edge body is configured to be displaced when the thrust reverser doors pivot from the stowed position to the deployed position.

First claim

What is claimed is:

1. An assembly for an aircraft propulsion system, comprising:
a target-type thrust reverser comprising a plurality of thrust reverser doors, each of the thrust reverser doors configured to pivot between a stowed position to a deployed position; and
a tubular trailing edge body configured to at least partially form a gas path nozzle for the aircraft propulsion system, the tubular trailing edge body forming an annular shape, an entirety of the tubular trailing edge body configured to be displaced when the thrust reverser doors pivot from the stowed position to the deployed position, the tubular trailing edge body maintaining the annular shape as the tubular trailing edge body is displaced, and the displacement of the tubular trailing edge body comprising a radial displacement relative to an axial centerline of the aircraft propulsion system.

2. The assembly of claim 1 , wherein the displacement of the tubular trailing edge body comprises an axial displacement relative to the axial centerline of the aircraft propulsion system.

3. The assembly of claim 1 , wherein the tubular trailing edge body is configured to completely form a trailing edge of the gas path nozzle.

4. The assembly of claim 1 , wherein
the tubular trailing edge body is configured to form a first portion of a trailing edge of the gas path nozzle; and
a first of the thrust reverser doors is configured to form a second portion of the trailing edge.

5. The assembly of claim 1 , further comprising:
a fixed structure;
wherein each of the thrust reverser doors is pivotally attached to the fixed structure by a respective hinge.

6. The assembly of claim 5 , wherein
the tubular trailing edge body is pivotally attached to a first of the thrust reverser doors by a hinge; and
the tubular trailing edge body is coupled to a second of the thrust reverser doors by a first linkage.

7. The assembly of claim 6 , wherein
the first linkage is configured as a link arm extending between a first link arm end and a second link arm end;
the link arm is pivotally attached to the second of the thrust reverser doors at the first link arm end; and
the link arm is pivotally attached to the tubular trailing edge body at the second link arm end.

8. The assembly of claim 6 , wherein the tubular trailing edge body is further coupled to the second of the thrust reverser doors by a second linkage, and the first linkage and the second linkage are circumferentially displaced from one another.

9. The assembly of claim 1 , wherein the tubular trailing edge body overlaps respective aft portions of the thrust reverser doors when the thrust reverser doors are in the stowed position.

10. The assembly of claim 1 , wherein
a gas path extends within the aircraft propulsion system to a trailing edge of the gas path nozzle;
each of the thrust reverser doors is configured to partially form an outer peripheral boundary of the gas path when in the stowed position; and
the tubular trailing edge body is configured to partially form the outer peripheral boundary of the gas path when the thrust reverser doors are in the stowed position.

11. The assembly of claim 1 , wherein the thrust reverser doors are configured to redirect gas flowing out from a core of the aircraft propulsion system.

12. The assembly of claim 1 , further comprising a plurality of actuators, each of the actuators configured to pivot a respective one of the thrust reverser doors from the stowed position to the deployed position.

13. An assembly for an aircraft propulsion system, comprising:
a target-type thrust reverser comprising a plurality of thrust reverser doors, each of the thrust reverser doors configured to pivot between a stowed position to a deployed position; and
a tubular trailing edge body configured to at least partially form a gas path nozzle for the aircraft propulsion system, the tubular trailing edge body forming an annular shape and configured to be displaced when the thrust reverser doors pivot from the stowed position to the deployed position, the tubular trailing edge body maintaining the annular shape as the tubular trailing edge body is displaced, and the displacement of the tubular trailing edge body comprising a pivotal displacement;
wherein a centerline of the tubular trailing edge body is non-coaxial with an axial centerline of the aircraft propulsion system when the tubular trailing edge body is displaced.

14. The assembly of claim 13 , wherein the displacement of the tubular trailing edge body further comprises
a radial displacement relative to the axial centerline of the aircraft propulsion system; and
an axial displacement relative to the axial centerline.

15. The assembly of claim 13 , wherein the tubular trailing edge body is configured to completely form a trailing edge of the gas path nozzle.

16. The assembly of claim 13 , wherein
the tubular trailing edge body is pivotally attached to a first of the thrust reverser doors by a hinge; and
the tubular trailing edge body is coupled to a second of the thrust reverser doors by a first linkage, the tubular trailing edge body is further coupled to the second of the thrust reverser doors by a second linkage, and the first linkage is circumferentially displaced from the second linkage.

17. An assembly for an aircraft propulsion system, comprising:
a fixed structure extending axially along and circumferentially about an axial centerline;
a first thrust reverser door pivotally attached to the fixed structure by a first hinge;
a second thrust reverser door pivotally attached to the fixed structure by a second hinge;
a trailing edge body configured to at least partially form a gas path nozzle for the aircraft propulsion system, the trailing edge body pivotally attached to the second thrust reverser door by a third hinge, the trailing edge body forming an annular shape, an entirety of the trailing edge body further configured to move relative to the fixed structure as the first blocker door and the second blocker door pivot from a stowed position to a deployed position, the trailing edge body maintaining the annular shape during the movement of the trailing edge body, and the movement of the trailing edge body comprising at least one of pivotal movement, or radial movement relative to the axial centerline; and
a linkage coupling the trailing edge body to the first thrust reverser door, the linkage pivotally attached to the trailing edge body and the first thrust reverser door.

18. The assembly of claim 17 , wherein the first thrust reverser door and the second thrust reverser door are configured to redirect gas flowing out from the aircraft propulsion system.

19. The assembly of claim 17 , wherein the trailing edge body is configured as a tubular trailing edge body.

20. An assembly for an aircraft propulsion system, comprising:
a target-type thrust reverser comprising a plurality of thrust reverser doors, each of the thrust reverser doors configured to pivot between a stowed position and a deployed position; and
a tubular trailing edge body forming an annular shape and configured to at least partially form a gas path nozzle for the aircraft propulsion system, the tubular trailing edge body configured to move from a first position to a second position as the thrust reverser doors pivot from the stowed position to the deployed position;
wherein a centerline of the tubular trailing edge body is coaxial with an axial centerline of the aircraft propulsion system when the tubular trailing edge body is in the first positi

Assignees

• Rohr Inc

Inventors

• Gormley Timothy

Classifications

• F02K1/60 Primary

  by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers · CPC title

• F02K1/605

  the aft end of the engine cowling being movable to uncover openings for the reversed flow · CPC title

• F02K1/763

  with actuating systems or actuating devices; Arrangement of actuators for thrust reversers · CPC title

• F02K1/70 Primary

  using thrust reverser flaps or doors mounted on the fan housing · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title