Systems and methods for altering inlet airflow of gas turbine engines

• US 9,169,779 B2
• Filed: 10/09/2007
• Issued: 10/27/2015
• Est. Priority Date: 10/09/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Winter, Michael
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): PRAGER, JESSE M
• Application Number:
  US11/869,040
• Publication Number:
  US 20090092482A1
• Time in Patent Office: 2,940 Days
• Field of Search: 415/126, 415/128, 415/150, 415/151, 415/157, 415/159, 415/914, 137/15.1, 137/15.2
• US Class Current: 1/1
• CPC Class Codes: F02C 7/042 having variable geometry
• CPC Class Codes: F02C 7/047 Heating to prevent icing
• CPC Class Codes: F02K 3/06 with front fan

Abstract

Systems and methods for altering airflow to gas turbine engines are provided. In this regard, a representative system includes a gas turbine engine inlet having a slat, the slat being movable between a retracted position and an extended position. In the extended position, the slat increases an effective diameter of the inlet compared to the diameter of the inlet when in the retracted position.

Claims

1. A system for altering inlet airflow to a gas turbine engine comprising:

a gas turbine engine inlet having a top side and a bottom side meeting at a leading edge thereof, and a slat, the slat being movable between a retracted position and an extended position;

in the extended position, the slat increasing an effective diameter of the inlet compared to the diameter of the inlet when in the retracted position; and

in the retracted position, said slat has an aft inner surface that conforms along its entire length to and rests atop a forward surface of the inlet on said lip over said top side and said bottom side beyond the leading edge thereof.

2. The system of claim 1, wherein:

the inlet comprises a slat assembly, the slat being a first slat of the slat assembly; and

the slat assembly comprises additional slats that are annularly arranged about a lip of the inlet.

3. The system of claim 2, wherein:

each of the slats is movable between a retracted position and an extended position;

the extended position of each of the slats is located radially outward, with respect to a centerline of the inlet, from a corresponding retracted position.

4. The system of claim 1, further comprising a pneumatic actuator operative to move the slat between the extended position and the retracted position.

5. The system of claim 4, further comprising a bleed air regulator operative to provide air to the pneumatic actuator for actuating the slat.

6. The system of claim 5, wherein the bleed air regulator is further operative to provide bleed air for anti-icing the inlet.

7. The system of claim 5, wherein:

the inlet defines an inlet plenum; and

the pneumatic actuator and bleed air regulator are located within the inlet plenum.

8. The system of claim 1, further comprising a gas turbine engine positioned to receive intake air via the inlet.

9. The system of claim 1, wherein the gas turbine engine is a turbofan.

10. A system for altering inlet airflow to a gas turbine engine comprising:

a slat configured as an annular segment, said annular segment having a generally parabolic shape; and

a slat actuator operative to move the slat between a retracted position in which said slat conforms along its entire length to and rests atop a lip and on a top and on a bottom of a leading edge of said inlet, and an extended position wherein;

the system further comprises a gas turbine engine inlet;

the slat is mounted to the inlet; and

in the extended position, the slat increases an effective diameter of the inlet compared to the diameter of the inlet when in the retracted position.

11. The system of claim 10, wherein:

the system comprises a slat assembly, the slat being a first slat of the slat assembly; and

the slat assembly comprises additional slats that are configured as annular segments.

12. The system of claim 11, wherein the slats of the slat assembly are pneumatically actuated.

13. The system of claim 12, further comprising a bleed air regulator operative to provide air for actuating at least one of the slats of the slat assembly.

14. The system of claim 13, wherein the bleed air regulator is further operative to provide bleed air for anti-icing the inlet.

15. The system of claim 12, wherein in the extended positions, the slats of the slat assembly are located radially outward from corresponding retracted positions.

16. A method for altering airflow to a gas turbine engine comprising:

selectively increasing an effective diameter of a nacelle inlet while a gas turbine engine mounted within the nacelle is operating wherein increasing the diameter comprises extending movable inlet slats located in a vicinity of the inlet and wherein decreasing said effective diameter of said nacelle inlet comprises resting said inlet slats that have an aft inner surface that conforms along its entire length and rests on a lip, a top surface and a bottom surface of a nacelle inlet at a leading edge thereof.

17. The method of claim 16, wherein extending movable inlet slats comprises using bleed air to move the slats.

18. The method of claim 17, further comprising additionally using the bleed air to anti-ice the inlet.

19. A system for altering inlet airflow to a gas turbine engine comprising:

a gas turbine engine inlet having a slat, the slat being movable between a retracted position and an extended position wherein the extended position, the slat increasing an effective diameter of the inlet compared to the diameter of the inlet when in the retracted position;

a pneumatic actuator operative to move the slat between the extended position and the retracted position;

a bleed air regulator operative to provide air to the pneumatic actuator for actuating the slat; and

,

wherein the inlet defines an inlet plenum and the pneumatic actuator and bleed air regulator are located within the inlet plenum.