Thrust reverse variable area fan nozzle

Patent metadata

Field	Value
Publication number	US-10001080-B2
Application number	US-201414462682-A
Country	US
Kind code	B2
Filing date	Aug 19, 2014
Priority date	Aug 19, 2014
Publication date	Jun 19, 2018
Grant date	Jun 19, 2018

Abstract

A thrust reverse variable area nozzle system for a nacelle of an aircraft engine system may include a reverse thrust opening disposed in the nacelle, and a thrust reverser door pivotally movable relative to the nacelle for selectively covering the reverse thrust opening, wherein the thrust reverser door is pivotally movable between a first position for completely covering the reverse thrust opening, a second position for partially uncovering a forward portion of the reverse thrust opening and discharging a bypass airflow through the forward portion of the reverse thrust opening in a forward direction, and a third position for partially uncovering an aft portion of the reverse thrust opening and discharging the bypass airflow through the aft portion of the reverse thrust opening in an aft direction.

First claim

What is claimed is:

1. A thrust reverse variable area nozzle system for a nacelle of an aircraft engine system, said system comprising:
a reverse thrust opening disposed in said nacelle; and
a thrust reverser door movably coupled to said nacelle for selectively covering said reverse thrust opening, said thrust reverser door comprising a forward end and an aft end;
a first slide-pivot connection selectively connecting said thrust reverser door and said nacelle and comprising a first slot, having an open first end and a closed second end, and a first pivot link movable within said first slot; and
a second slide-pivot connection selectively connecting said thrust reverser door and said nacelle and comprising a second slot, having a closed first end and a closed second end, and a second pivot link movable within said second slot; and
wherein said thrust reverser door is pivotally movable between:
a first position, in which said first pivot link is seated in said closed second end of said first slot and said second pivot link is seated in said closed second end of said second slot and said thrust reverser door completely covers said reverse thrust opening;
a second position, in which said first pivot link is removed from said first slot through said open first end of said first slot and said second pivot link is seated in said closed second end of said second slot and said thrust reverser door pivots about said second pivot link to position said forward end of said thrust reverser door radially outward and said aft end of said thrust reverser door radially inward to partially uncover a forward portion of said reverse thrust opening; and
a third position, in which said first pivot link is seated in said closed second end of said first slot and said second pivot link is seated in said closed first end of said second slot and said thrust reverser door pivots about said first pivot link to position said aft end of said thrust reverser door radially outward to partially uncover an aft portion of said reverse thrust opening.

2. The system of claim 1 further comprising a pivot mechanism operable to control movement of the thrust reverser door between said first position, said second position, and said third position.

3. The system of claim 2 wherein said pivot mechanism comprises
an actuator coupled to said thrust reverser door to selectively control pivotal motion of said thrust reverser about one of the first pivot link or said second pivot link.

4. The system of claim 3 , wherein said actuator comprises a linear actuator.

5. The system of claim 1 wherein each one of said first slot and said second slot is
linear.

6. The system of claim 1 wherein:
said nacelle comprises a nacelle frame;
said thrust reverser door comprises a door frame;
said first slot is located in one of said nacelle frame or said door frame;
said first pivot link is located on an opposing one of said nacelle frame or said door frame;
said second slot is located in said one of said nacelle frame or said door frame; and
said second pivot link is located on said opposing one of said nacelle frame or said door frame.

7. The system of claim 1 wherein:
said first slide-pivot connection is located toward said forward end of said thrust reverser door and defines a forward pivot axis of said thrust reverser door; and
said second slide-pivot connection is spaced away from said aft end of said thrust reverser door and defines an aft pivot axis of said thrust reverser door.

8. The system of claim 1 wherein:
said forward pivot axis is defined through said thrust reverser door and is fixed relative to said nacelle; and
said aft pivot axis is defined through said thrust reverser door and is fixed relative to said nacelle.

9. The system of claim 1 wherein:
with said thrust reverser door in said second position, a bypass airflow, passing through said nacelle, is at least partially discharged through said forward portion of said reverse thrust opening in a forward direction; and
with said thrust reverser door in said third position, said bypass airflow is at least partially discharged through said aft portion of said reverse thrust opening in an aft direction.

10. An engine system for an aircraft, said system comprising:
an engine;
a nacelle comprising an inner cowling extending circumferentially around said engine and an outer cowling extending circumferentially around said inner cowling;
a bypass airflow passage defined between said inner cowling and said outer cowling;
a reverse thrust opening disposed in said outer cowling and in fluid communication with said bypass airflow passage; and
a thrust reverser door movably coupled to said outer cowling for selectively covering said reverse thrust opening, said thrust reverser door comprising a forward end and an aft end, opposite said forward end;
a first slide-pivot connection selectively connecting said thrust reverser door and said nacelle and comprising a first slot, having an open first end and a closed second end, and a first pivot link movable within said first slot; and
a second slide-pivot connection selectively connecting said thrust reverser door and said nacelle and comprising a second slot, having a closed first end and a closed second end, and a second pivot link movable within said second slot; and
wherein said thrust reverser door is pivotally movable between:
a first position, in which said first pivot link is seated in said closed second end of said first slot and said second pivot link is seated in said closed second end of said second slot and said thrust reverser door completely covers said reverse thrust opening;
a second position, in which said first pivot link is removed from said first slot through said open first end of said first slot and said second pivot link is seated in said closed second end of said second slot and said thrust reverser door pivots about said second pivot link to position said forward end of said thrust reverser door radially outward and said aft end of said thrust reverser door radially inward, within said bypass airflow passage, to partially uncover a forward portion of said reverse thrust opening; and
a third position, in which said first pivot link is seated in said closed second end of said first slot and said second pivot link is seated in said closed first end of said second slot and said thrust reverser door pivots about said first pivot link to position said aft end of said thrust reverser door radially outward to partially uncover an aft portion of said reverse thrust opening.

11. The system of claim 10 further comprising a pivot mechanism operatively coupled to said thrust reverser door and to said nacelle to selectively control pivotal motion of the thrust reverser door, about one of the first pivot link or said second pivot link, between said first position, said second position, and said third position.

12. The system of claim 11 wherein said pivot mechanism comprises: a linear actuator connected to said thrust reverser door.

13. The system of claim 10 wherein:
said first slide-pivot connection is located proximate to said forward end of said thrust reverser door and defines a forward pivot axis of said thrust reverser door; and
a second slide-pivot connection is spaced away from said aft end of said thrust reverser door and defines and aft pivot axis of said thrust reverser door.

14. The system of claim 10 wherein at least one of
said first slot
and
said second slot
is linear.

15. The system of claim 10 wherein:
said first pivot link moves linearly within said first slot and said second pivot li

Assignees

• Boeing Co

Inventors

• Cerra David F
• Willie Robert H

Classifications

• F02K1/11

  by means of pivoted eyelids · CPC title

• F05D2260/50

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

• F02K1/70

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

• F02K1/763

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

• F02K1/1207 Primary

  of one series of flaps hinged at their upstream ends on a fixed structure (F02K1/1215 - F02K1/1292 take precedence) · CPC title