Thrust reverser system with hidden blocker doors

Patent metadata

Field	Value
Publication number	US-10655564-B2
Application number	US-201615154516-A
Country	US
Kind code	B2
Filing date	May 13, 2016
Priority date	May 13, 2016
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

An assembly is provided for an aircraft propulsion system with an axial centerline. This assembly includes a nacelle structure and a thrust reverser system. The nacelle structure includes a fan cowl, where a forward cavity extends axially into the nacelle structure from an aft end of the fan cowl. The thrust reverser system includes a sleeve, a cascade structure, a blocker door and a linkage. The sleeve is configured to translate axially along the centerline and relative to the nacelle structure between a forward stowed position and an aft deployed position. The cascade structure, the blocker door and the linkage are at least partially within the forward cavity when the sleeve is in the forward stowed position. The cascade structure is fixedly attached to the sleeve. The linkage extends between and is pivotally attached to the cascade structure and the blocker door.

First claim

I claim:

1. An assembly for an aircraft propulsion system with an axial centerline, comprising:
a nacelle structure including a fan cowl, a forward cavity extending axially into the nacelle structure from an aft end of the fan cowl; and
a thrust reverser system including a sleeve, a cascade structure, a blocker door and a linkage;
the sleeve configured to translate axially along the centerline and relative to the nacelle structure between a forward stowed position and an aft deployed position; and
the cascade structure, the blocker door and the linkage at least partially within the forward cavity when the sleeve is in the forward stowed position;
the cascade structure fixedly attached to the sleeve such that a position of the cascade structure relative to the sleeve remains constant as the sleeve translates from the forward stowed position to the aft deployed position;
the linkage extending between and pivotally attached to the cascade structure and the blocker doors;
the blocker door configured to move axially out of the forward cavity as the sleeve translates axially from the forward stowed position to an intermediate position; and
a forward end of the blocker door configured to swing radially inward into a bypass gas path of the aircraft propulsion system as the sleeve axially translates from the intermediate position to the aft deployed position.

2. The assembly of claim 1 , wherein the linkage is operable to cause the forward end of the blocker door to swing radially inward into the bypass gas path.

3. The assembly of claim 1 , wherein
a forward end of the linkage is pivotally attached to the cascade structure and is operable to move axially as the sleeve translates axially from the forward stowed position to the aft deployed position; and
an aft end of the linkage is pivotally attached to the blocker door and is operable to move axially and radially inward as the sleeve translates axially from the intermediate position to the aft deployed position.

4. The assembly of claim 3 , wherein the aft end of the linkage is further operable to move axially as the sleeve translates axially from the forward stowed position to the intermediate position.

5. The assembly of claim 1 , wherein the thrust reverser system further includes a device configured to initiate the radially inward swinging of the forward end of the blocker door.

6. The assembly of claim 1 , wherein
the thrust reverser system further includes a door carrier arranged with the sleeve;
the blocker door is pivotally attached to the door carrier and extends between the linkage and the door carrier; and
the door carrier is configured to move axially as the sleeve translates axially from the forward stowed position to the intermediate position, and is configured to be stationary as the sleeve translates axially from about the intermediate position to the aft deployed position.

7. The assembly of claim 1 , wherein
the thrust reverser system further includes a door carrier arranged with the sleeve;
the blocker door is pivotally attached to the door carrier and extends between the linkage and the door carrier; and
the door carrier is configured to move axially with the sleeve as the sleeve translates axially from the forward stowed position to the intermediate position, and is configured to move axially relative to the sleeve as the sleeve translates axially from the intermediate position to the aft deployed position.

8. The assembly of claim 1 , wherein the cascade structure is within the forward cavity and/or the linkage is within the forward cavity when the sleeve is in the forward stowed position.

9. The assembly of claim 1 , wherein the blocker door is partially within the forward cavity when the sleeve is in the forward stowed position.

10. The assembly of claim 1 , wherein
an aft cavity extends axially into the sleeve from a forward end of the sleeve; and
a forward end portion of the blocker door is within the forward cavity and an aft end portion of the blocker door is within the aft cavity when the sleeve is in the forward stowed position.

11. The assembly of claim 10 , wherein
the thrust reverser system further includes a door carrier within the aft cavity;
the blocker door is pivotally attached to the door carrier and extends between the linkage and the door carrier; and
the door carrier is configured to selectively move axially relative to the nacelle structure and the sleeve.

12. The assembly of claim 1 , wherein the nacelle structure further includes a torque box, and the forward cavity is formed radially between the torque box and the fan cowl.

13. The assembly of claim 1 , wherein the thrust reverser system further includes a second linkage that extends between and is pivotally attached to the cascade structure and the blocker door, and the second linkage is within the forward cavity when the sleeve is in the forward stowed position.

14. An assembly for an aircraft propulsion system with an axial centerline, comprising:
a fan case;
a fan cowl covering the fan case, wherein a forward cavity is radially between the fan case and the fan cowl; and
a thrust reverser system including a sleeve, a cascade structure, a blocker door and a linkage;
the sleeve configured to translate axially along the centerline and relative to the fan cowl between a forward stowed position and an aft deployed position; and
the cascade structure, the blocker door and the linkage at least partially within the forward cavity when the sleeve is in the forward stowed position;
the cascade structure configured to move axially with the sleeve as the sleeve translates axially from the forward stowed position to the aft deployed position; and
the linkage extending between and pivotally attached to the cascade structure and the blocker door;
the blocker door configured to move axially out of the forward cavity as the sleeve translates axially from the forward stowed position to an intermediate position;
a forward end of the blocker door configured to swing radially inward into a bypass gas path of the aircraft propulsion system as the sleeve axially translates from the intermediate position to the aft deployed position;
the thrust reverser system further including a door carrier arranged with the sleeve;
the blocker door pivotally attached to the door carrier and extending between the linkage and the door carrier; and
the door carrier configured to move axially with the sleeve as the sleeve translates axially from the forward stowed position to about the intermediate position, and the door carrier configured to be stationary as the sleeve translates axially from about the intermediate position to the aft deployed position.

15. The assembly of claim 14 , wherein
an aft cavity extends axially into the sleeve from a forward end of the sleeve;
a forward end portion of the blocker door is within the forward cavity and an aft end portion of the blocker door is within the aft cavity when the sleeve is in the forward stowed position; and
the door carrier is within the aft cavity.

16. The assembly of claim 14 , wherein the cascade structure is fixed relative to the sleeve.

17. The assembly of claim 1 , wherein the cascade structure contacts the sleeve.

Assignees

• Rohr Inc

Inventors

• Gormley Timothy

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

• F02K1/763

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

• F05D2250/36

  in inner-outer relationship, e.g. shaft-bearing arrangements · CPC title

• F05D2250/42

  with two degrees of freedom · CPC title

• F02K3/06

  with front fan · CPC title