VARIABLE AREA FAN NOZZLE THRUST REVERSER

• US 20090193789A1
• Filed: 10/12/2006
• Published: 08/06/2009
• Est. Priority Date: 10/12/2006
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Pero, Edward B.
• Granted Patent: US 8,151,551 B2
• Time in Patent Office: Days
• US Class Current: 60/226.2
• CPC Class Codes: F02K 1/70 using thrust reverser flaps or doors mounted on the fan housing

Abstract

A nozzle for use in a gas turbine engine includes nozzle doors coupled with a fan nacelle wherein the nozzle doors move in unison between a plurality of positions to influence a bypass airflow through a fan bypass passage. A linkage connects the nozzle doors and an actuator. A louver section coupled with the linkage moves in unison with the nozzle doors between a plurality of louver positions to direct a portion of the bypass airflow in a selected direction.

Claims

1. A nozzle for use in a gas turbine engine, comprising:

first and second nozzle doors that move in unison between a plurality of positions to influence a bypass airflow through a fan bypass passage;

a louver section that moves in unison with the nozzle doors between a plurality of louver positions;

a linkage connecting the nozzle doors and the louver section; and

an actuator coupled with the linkage, wherein the actuator is selectively operative to move the nozzle doors and the louver section in unison using the linkage.

2. The nozzle as recited in claim 1, wherein the first nozzle door is radially outwards of the second nozzle door relative to an engine centerline axis.

3. The nozzle as recited in claim 2, wherein the linkage includes a link that is slidably connected to each of the nozzle doors.

4. The nozzle as recited in claim 3, wherein the linkage includes another link having one end that is pivotally connected with the link and another end that is pivotally connected with the actuator.

5. The nozzle as recited in claim 1, wherein the linkage includes a link having a first linear section that extends in a first lengthwise direction and a second linear section that extends in a second lengthwise direction that is transverse to the first lengthwise direction.

6. The nozzle as recited in claim 1, wherein the first nozzle door includes a linear slot and the second nozzle door includes a non-linear, wherein the linear slot and the non-linear slot are slidably connected with the linkage.

7. The nozzle as recited in claim 1, wherein each of the nozzle doors are each moveable about a pivot point.

8. The nozzle as recited in claim 7, wherein the first nozzle door moves in an aft direction about its pivot point in unison with movement of the second nozzle door in a forward direction about its pivot point.

9. The nozzle as recited in claim 1, wherein the louver section directs the bypass airflow in a forward direction in one of the plurality of louver positions and directs the bypass airflow in an aft direction in another of the plurality of positions.

10. The nozzle as recited in claim 1, wherein the louver section includes a plurality of louvers that are each moveable about corresponding pivots, each of the plurality of louvers including an end that is connected with a link rod that connects to the linkage, wherein movement of the linkage causes movement of the link rod such that the plurality of louvers move about the pivots.

13. The gas turbine engine system as recited in claim 1, wherein the first nozzle door extends in a radially outward direction from the nacelle relative to a centerline axis of the gas turbine engine core and the second nozzle door extends in a radial inward direction into the fan bypass passage, in the intermediate position and the thrust reverse position.

14. The gas turbine engine system as recited in claim 13, wherein the nozzle doors direct the bypass airflow in an aft direction to provide thrust while in the intermediate position, and the nozzle doors direct the bypass airflow in a forward direction to produce a thrust reversing force in the thrust reverse position.

11. A gas turbine engine system comprising:

a fan;

a nacelle arranged about the fan;

a gas turbine engine core having a compressor and a turbine at least partially within the nacelle;

a fan bypass passage downstream of the fan for conveying a bypass airflow, between the nacelle and the gas turbine engine core;

first and second nozzle doors associated with the fan bypass passage that move in unison between a stowed position, an intermediate position, and a thrust reverse position to influence the bypass airflow;

a louver section that moves in unison with the first and second nozzle doors between a plurality of louver positions;

a linkage connecting the nozzle doors and the louver section;

an actuator coupled with the linkage; and

a controller that selectively commands the actuator to move the nozzle doors and the louver section in unison using the linkage.

12. The gas turbine engine system as recited in claim 11, wherein the stowed position corresponds to an aircraft cruise condition, the intermediate position corresponds to an aircraft take-off condition, and the thrust reverse position corresponds to an aircraft condition after landing.

15. The gas turbine engine system as recited in claim 11, wherein movement of the nozzle doors changes a variable cross-sectional area associated with the fan bypass passage to influence the bypass airflow.

16. A method of controlling a gas turbine engine system disposed about a centerline axis and having a fan bypass passage for conveying a bypass airflow, comprising the steps of:

moving a first nozzle door, a second nozzle door that is located radially inwards of the first nozzle door relative to the centerline axis, and a louver section in unison between a plurality of positions to influence the bypass airflow through the fan bypass passage.

17. The method recited in claim 16, including moving the first nozzle % door and the second nozzle door to change a cross-sectional-area associated with the fan bypass passage.

18. The method recited in claim 16, including moving the first nozzle door and the second nozzle door to a position that deflects the bypass airflow in a forward direction to produce a thrust reversing force.

19. The method recited in claim 16, including moving a linkage to move the first nozzle door and the second nozzle in unison with the louver section connected to the linkage.