Variable contour nacelle assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9228534-B2
Application number	US-77228707-A
Country	US
Kind code	B2
Filing date	Jul 2, 2007
Priority date	Jul 2, 2007
Publication date	Jan 5, 2016
Grant date	Jan 5, 2016

Abstract

A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The portion of the nacelle assembly including the adjustable contour is selectively moveable between a first portion and a second position to influence the adjustable contour of the nacelle assembly. A controller identifies an abnormal aircraft operating condition and selectively moves the portion of the nacelle assembly including the adjustable contour between the first position and the second position in response to detecting the abnormal aircraft operating condition.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a compressor section, a combustor section, and a turbine section;
a nacelle assembly at least partially surrounding at least one of said compressor section, said combustor section and said turbine section, wherein said nacelle assembly includes an inlet lip section and a cowl section that each include an adjustable contour, each of said inlet lip section and said cowl section including a first surface that faces radially inward and a second surface that faces radially outward, each of said first surfaces and said second surfaces being moveable to influence said adjustable contours; and
a controller that identifies an abnormal aircraft operating condition, wherein said controller selectively moves said inlet lip section and said cowl section of said nacelle assembly in response to detecting said abnormal aircraft operating condition.

2. The gas turbine engine as recited in claim 1 , wherein said abnormal aircraft operating condition includes at least one of a windmilling engine-out condition, a crosswind take-off condition, a fan blade-out condition, a high angle of attack condition and a yaw condition.

3. The gas turbine engine as recited in claim 1 , comprising a sensor that produces a signal representing said abnormal aircraft operating condition and communicates said signal to said controller.

4. The gas turbine engine as recited in claim 1 , comprising an actuator assembly in communication with said controller to move said nacelle assembly in response to detecting said abnormal aircraft operating condition.

5. The gas turbine engine as recited in claim 4 , comprising at least one of an internal linkage, a plurality of bellows and a shape memory alloy that is actuated by said actuator assembly to influence said adjustable contours.

6. The gas turbine engine as recited in claim 1 , wherein at least one of said first surfaces and said second surfaces are moveable between a first position and a second position, and said second position is axially upstream relative to said first position.

7. The gas turbine engine as recited in claim 1 , wherein at least one of said first surfaces and said second surfaces are moveable between a first position and a second position, and said second position is radially outward relative to said first position.

8. The gas turbine engine as recited in claim 1 , wherein said inlet lip section is pivoted relative to said cowl section, wherein said inlet lip section is inwardly pivoted at an angle relative to a plane positioned at a foremost end of said nacelle assembly.

9. The gas turbine engine as recited in claim 1 , comprising a plurality of bellows that influence said adjustable contours.

10. The gas turbine engine as recited in claim 1 , comprising a shape memory alloy that influences said adjustable contours.

11. The gas turbine engine as recited in claim 1 , wherein said abnormal aircraft operating condition includes at least one of a windmilling engine-out condition, a fan blade-out condition, a high angle of attack condition and a yaw condition.

12. The gas turbine engine as recited in claim 1 , wherein said abnormal aircraft operating condition is a windmilling engine-out condition.

13. The gas turbine engine as recited in claim 1 , wherein said abnormal aircraft operating condition is a crosswind condition.

14. The gas turbine engine as recited in claim 1 , wherein said abnormal aircraft operating condition is a fan blade-out condition.

15. The gas turbine engine as recited in claim 1 , wherein said abnormal aircraft operating condition is a yaw condition.

16. The gas turbine engine as recited in claim 1 , wherein said first surfaces and said second surfaces are moveable between a first position and a second position, and said second position is both axially upstream and readily outward relative to said first position.

Assignees

• Jain Ashok K
• Winter Michael
• United Technologies Corp

Inventors

• Jain Ashok K
• Winter Michael

Classifications

• Y10T137/0645

  With condition responsive control means · CPC title

• F05D2300/505

  Shape memory behaviour · CPC title

• F05D2270/64

  Hydraulic actuators · CPC title

• F02K3/06 Primary

  with front fan · CPC title

• F02C7/042

  having variable geometry · CPC title