Mixed flow exhaust thrust reverser with area control nozzle systems and methods

Patent metadata

Field	Value
Publication number	US-12497932-B2
Application number	US-202418922109-A
Country	US
Kind code	B2
Filing date	Oct 21, 2024
Priority date	Nov 22, 2021
Publication date	Dec 16, 2025
Grant date	Dec 16, 2025

Abstract

A thrust reverser includes an outer articulating panel and an inner articulating panel. The outer articulating panel includes an outer thrust reverser door pivotally coupled to the outer articulating panel. The outer thrust reverser door is movable between an outer door stowed position and an outer door deployed position with respect to the outer articulating panel. The inner articulating panel includes an inner thrust reverser door pivotally coupled to the inner articulating panel. The inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel. The inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses to generate reverse thrust to an aircraft when the thrust reverser doors are in the deployed positions.

First claim

The invention claimed is:

1 . A thrust reverser, comprising:
an outer articulating panel comprising an outer thrust reverser door pivotally coupled to the outer articulating panel, the outer thrust reverser door is movable between an outer door stowed position and an outer door deployed position with respect to the outer articulating panel to create a first opening in the outer articulating panel; and an inner articulating panel positioned radially inward of the outer articulating panel relative to an engine central longitudinal axis and comprising an inner thrust reverser door pivotally coupled to the inner articulating panel, the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel to create a second opening in the inner articulating panel; wherein the inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses through the second opening and the first opening in a direction having a forward component to generate reverse thrust to an aircraft.

2 . The thrust reverser of claim 1 , wherein the inner articulating panel further comprises a forward inner skin and an aft inner skin.

3 . The thrust reverser of claim 2 , wherein a nozzle throat is at least partially defined at an interface between the forward inner skin and the aft inner skin.

4 . The thrust reverser of claim 3 , wherein the forward inner skin is configured to pivot to vary a nozzle throat area.

5 . The thrust reverser of claim 3 , further comprising a sliding joint offset from the interface between the forward inner skin and the aft inner skin, wherein the forward inner skin and the aft inner skin are coupled together at the sliding joint.

6 . The thrust reverser of claim 2 , further comprising a first thrust reverser actuator configured to pivot the outer thrust reverser door with respect to the outer articulating panel between the outer door deployed position and the outer door stowed position.

7 . The thrust reverser of claim 6 , further comprising a second thrust reverser actuator configured to pivot the inner thrust reverser door with respect to the inner articulating panel between the deployed inner door position and the stowed inner door position.

8 . The thrust reverser of claim 7 , further comprising a first nozzle actuator configured to pivot the outer articulating panel.

9 . The thrust reverser of claim 8 , further comprising a second nozzle actuator configured to pivot the forward inner skin.

10 . The thrust reverser of claim 9 , further comprising:
a first linear joint disposed between the first nozzle actuator and the outer articulating panel; and a second linear joint disposed between the second nozzle actuator and the forward inner skin.

11 . The thrust reverser of claim 8 , wherein the first nozzle actuator is pivotably coupled to an interior of the outer articulating panel.

12 . The thrust reverser of claim 9 , wherein the second nozzle actuator is pivotably coupled to an interior of the forward inner skin.

13 . The thrust reverser of claim 10 , further comprising:
a third linear joint disposed between the first thrust reverser actuator and the outer thrust reverser door; and a fourth linear joint disposed between the second thrust reverser actuator and the inner thrust reverser door.

14 . The thrust reverser of claim 2 , wherein the forward inner skin is pivotably coupled to a forward bulkhead.

15 . The thrust reverser of claim 1 , wherein a nozzle exit is at least partially defined at an aft end of the inner articulating panel.

16 . The thrust reverser of claim 15 , wherein the outer articulating panel is configured to pivot to vary a nozzle exit area.

17 . The thrust reverser of claim 1 , wherein the outer articulating panel further comprises an outer skin.

18 . The thrust reverser of claim 17 , further comprising a flap located at a forward edge of the outer skin, wherein the flap is slidingly coupled to the outer skin to maintain a continuous aerodynamic surface while the outer articulating panel pivots.

Assignees

• Rohr Inc

Inventors

• Schrell Johann Steven

Classifications

• F05D2260/605

  Venting into the ambient atmosphere or the like · CPC title

• F05D2260/57

  using servos, independent actuators, etc. · CPC title

• F05D2240/128

  Nozzles · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/763

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