Integrated actuator module for gas turbine engine

• US 8,210,800 B2
• Filed: 06/12/2008
• Issued: 07/03/2012
• 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): LE, DUNG ANH
• Application Number:
  US12/138,370
• Publication Number:
  US 20090317229A1
• Time in Patent Office: 1,482 Days
• Field of Search: 415/65, 415/66, 415/68, 415/69, 415160-161, 415/148, 415/149.4, 415/150, 415/151, 415/145, 415/159
• US Class Current: 415/145
• 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: F02C 9/20 by throttling; by adjusting vanes
• CPC Class Codes: F04D 27/0215 Arrangements therefor, e.g. bleed or by-pass valves
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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 at least one low pressure compressor variable vane set; and

a second actuator mounted within said actuator housing, said second actuator operable to actuate at least one high pressure compressor 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. A gas turbine engine comprising:

an engine static structure;

a multiple of low pressure compressor variable vane sets supported by said engine static structure;

a multiple of high pressure compressor variable vane sets supported by said engine static structure;

an actuator housing mountable to said engine static structure;

a first actuator mounted within said actuator housing, said first actuator operable to actuate at least one of said multiple of low pressure compressor variable vane sets; and

a second actuator mounted within said actuator housing, said second actuator operable to actuate at least one of said multiple of high pressure compressor variable vane sets.

8. The engine as recited in claim 7, wherein said actuator housing is mountable to said engine static structure axially between a low pressure compressor and a high pressure compressor.

9. The engine as recited in claim 7, wherein said actuator housing is mountable within an annulus defined between a multiple of circumferentially spaced radially extending struts and a multiple of struts within an inner frame of an intermediate case (IMC) of said engine static structure.

10. The engine as recited in claim 7, wherein said actuator housing is mountable within an annulus defined between a multiple of circumferentially spaced radially extending struts and a multiple of struts within an inner frame of said engine static structure.

11. The engine as recited in claim 7, further comprising an accessory gearbox mounted to said engine static structure, said actuator housing mountable to said accessory gearbox.

12. A method of actuating a variable vane system for a gas turbine engine comprising:

actuating a multiple of variable vane sets with a respective multiple of actuators, each of the multiple of actuators mounted within a common actuator housing.

13. A method as recited in claim 12, further comprising:

mounting the actuator housing to an engine static structure axially between a low pressure compressor and a high pressure compressor.

14. A method as recited in claim 12, further comprising:

mounting the actuator housing to an accessory gearbox mounted to an engine static structure.

15. A method as recited in claim 14, further comprising:

mounting the actuator housing between lobes of the accessory gearbox.

16. A method as recited in claim 12, further comprising:

mounting the actuator housing to an intermediate case (IMC) of an engine static structure.

17. A method as recited in claim 12, further comprising:

mounting the actuator housing within an annulus defined between a multiple of circumferentially spaced radially extending struts and a multiple of struts within an inner frame of an intermediate case (IMC) of an engine static structure.