Integrated actuator module for gas turbine engine

• US 9,097,137 B2
• Filed: 12/15/2011
• Issued: 08/04/2015
• Est. Priority Date: 06/12/2008
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Suciu, Gabriel L., Merry, Brian D., Dye, Christopher M., Elder, James S.
• Primary Examiner(s): White, Dwayne J
• Assistant Examiner(s): GRIGOS, WILLIAM G
• Application Number:
  US13/327,722
• Publication Number:
  US 20120087780A1
• Time in Patent Office: 1,328 Days
• Field of Search: 415/145, 415/149.4, 415/150, 415/151, 415/160, 415/161
• US Class Current: 1/1
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps

Abstract

An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing.

Claims

1. An actuator module for a gas turbine engine comprising:

an actuator housing;

a first actuator mounted within said actuator housing, said first actuator operable to actuate a first variable vane set; and

a second actuator mounted within said actuator housing, said second actuator operable to actuate a second variable vane set.

2. The actuator module as recited in claim 1, further comprising a third actuator mounted within said actuator housing, said third actuator operable to actuate a bleed valve system.

3. The actuator module as recited in claim 2, wherein said bleed valve system comprises a 2.5 bleed valve actuator system.

4. The actuator module as recited in claim 1, wherein said actuator housing is mountable to an accessory gearbox.

5. The actuator module as recited in claim 1, wherein said actuator housing is mountable to an engine static structure.

6. The actuator module as recited in claim 1, wherein said actuator housing is mountable to an intermediate case (IMC).

7. The actuator module as recited in claim 1, wherein said first variable vane set is a low pressure compressor variable vane set.

8. The actuator module as recited in claim 1, wherein said second variable vane set is a high pressure compressor variable vane set.

9. A gas turbine engine comprising:

a static structure;

a core engine;

a gear system supported by said static structure;

a fan section driven by said core engine through said gear system;

an actuator housing mounted to said static structure;

a first actuator mounted within said actuator housing, said first actuator operable to actuate a first variable vane set of said core engine; and

a second actuator mounted within said actuator housing, said second actuator operable to actuate at least one second variable vane set.

10. The engine as recited in claim 9, wherein said first variable vane set is a low pressure compressor variable vane set.

11. The engine as recited in claim 9, wherein said second variable vane set is a high pressure compressor variable vane set.

12. The engine as recited in claim 9, wherein said gear system defines a gear reduction ratio of greater than or equal to about 2.3.

13. The engine as recited in claim 9, wherein said gear system defines a gear reduction ratio of greater than or equal to about 2.5.

14. The engine as recited in claim 9, wherein said gear system defines a gear reduction ratio of greater than or equal to 2.5.

15. The engine as recited in claim 9, wherein said core engine includes a low pressure turbine which defines a pressure ratio that is greater than about five (5).

16. The engine as recited in claim 9, wherein said core engine includes a low pressure turbine which defines a pressure ratio that is greater than five (5).

17. The engine as recited in claim 9, wherein said fan section is mounted within a fan nacelle and said core engine is mounted within a core nacelle, said fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path for a fan bypass airflow, said fan bypass airflow defines a bypass ratio greater than about six (6).

18. The engine as recited in claim 17, wherein said bypass airflow defines a bypass ratio greater than about ten (10).

19. The engine as recited in claim 18, wherein said bypass flow defines a bypass ratio greater than ten (10).