Internally actuated inlet guide vane for fan section

• US 8,915,703 B2
• Filed: 07/28/2011
• Issued: 12/23/2014
• Est. Priority Date: 07/28/2011
• Status: Expired due to Fees

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Mohammed, Sohail
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): BROCKMAN, ELDON T
• Application Number:
  US13/192,517
• Publication Number:
  US 20130028715A1
• Time in Patent Office: 1,244 Days
• Field of Search: 415/148, 415/150, 415/155, 415/159, 415/160, 415/161, 415/162, 415/163, 415/164, 415/165, 415/166
• US Class Current: 415/160
• 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

A variable inlet guide vane assembly includes a plurality of circumferentially spaced inlet guide vanes mounted to pivot to change an angle of the guide vanes relative to an air flow. An actuator actuates the plurality of inlet guide vanes to change the angle, and is positioned radially inward of the inlet guide vanes.

Claims

1. A variable inlet guide vane assembly comprising:

a plurality of circumferentially spaced inlet guide vanes mounted to pivot and change an angle of the guide vanes relative to an air flow;

an actuator configured to actuate said plurality of inlet guide vanes to change the angle, said actuator being positioned radially inward of said inlet guide vanes;

said actuator driving a cam ring, said cam ring moving a link associated with each of said inlet guide vanes, to change the angle;

said actuator driving a piston rod, said piston rod being secured to said cam ring such that said cam ring moves with said piston rod; and

there is no actuator radially outward of said inlet guide vanes to provide a smaller envelope.

2. The assembly as set forth in claim 1, wherein said cam ring has a slot which carries a roller associated with each of the links.

3. The assembly as set forth in claim 1, wherein said cam ring is moved axially and causes said links to move said inlet guide vanes to pivot, and thus change said angle.

4. The assembly as set forth in claim 2, wherein a roller cage is positioned to ride with the cam slot.

5. The assembly as set forth in claim 4, wherein said roller cage is formed of a material having self-lubricating properties.

6. The assembly as set forth in claim 1, wherein said actuator is one of a hydraulic or electric actuator.

7. The assembly as set forth in claim 1, wherein said actuator is to be positioned outwardly of an end of a shaft for driving a rotor associated with the variable inlet guide vane assembly.

8. The assembly as set forth in claim 1, wherein said inlet guide vane assembly is to be utilized as part of a gas turbine engine fan section.

9. A gas turbine engine comprising:

a turbine section;

a combustor section;

a compressor section; and

a fan section including a plurality of rotor blades rotating with a rotor, and a plurality of circumferentially spaced inlet guide vanes positioned to be upstream of said rotor blades, said inlet guide vanes mounted to pivot to change an angle of the guide vanes relative to an air flow, an actuator for actuating said plurality of inlet guide vanes to change the angle, said actuator being positioned radially inward of said variable inlet guide vanes;

said actuator driving a cam ring, said cam ring moving a link associated with each of said inlet guide vanes, to change the angle;

said actuator driving a piston rod, said piston rod being secured to said cam ring such that said cam ring moves with said piston rod; and

there is no actuator radially outward of said inlet guide vanes to provide a smaller envelope.

10. The gas turbine engine as set forth in claim 9, wherein said cam ring has a slot which carries a roller associated with each of the links.

11. The gas turbine engine as set forth in claim 9, wherein said cam ring is moved axially and causes said links to move said inlet guide vanes to pivot, and thus change said angle.

12. The gas turbine engine as set forth in claim 9, wherein said actuator is one of a hydraulic or electric actuator.

13. The assembly as set forth in claim 10, wherein a roller cage is positioned to ride with the cam slot.

14. The assembly as set forth in claim 13, wherein said roller cage is formed of a material having self-lubricating properties.

15. The assembly as set forth in claim 9, wherein said actuator is positioned outwardly of an end of a shaft for driving the rotor.

16. A variable inlet guide vane assembly comprising:

a plurality of circumferentially spaced inlet guide varies mounted to pivot and change an angle of the guide vanes relative to an air flow;

an actuator configured to actuate said plurality of inlet guide vanes to change the angle, said actuator being positioned radially inward of said inlet guide vanes;

said actuator driving a cam ring, said cam ring moving a link associated with each of said inlet guide vanes, to change the angle;

said actuator driving a piston rod, said piston rod being secured to said cam ring such that said cam ring moves with said piston rod;

said cam ring has a slot which carries a roller associated with each of the links, and

a single slot carries a plurality of said rollers, with one said roller associated with each of the links.

17. The assembly as set forth in claim 16, wherein there is no actuator radially outward of said inlet guide vanes to provide a smaller envelope.

18. A gas turbine engine comprising:

a turbine section;

a combustor section;

a compressor section;

a fan section including a plurality of color blades rotating with a rotor, and a plurality of circumferentially spaced inlet guide vanes positioned to be upstream of said rotor blades, said inlet guide vanes mounted to pivot to change an angle of the guide vanes relative to an air flow, an actuator for actuating said plurality of inlet guide vanes to change the angle, said actuator being positioned radially inward of said variable inlet guide vanes;

said actuator driving a cam ring, said cam ring moving a link associated with each of said inlet guide vanes, to change the angle;

said actuator driving a piston rod, said piston rod being secured to said cam ring such that said cam ring moves with said piston rod;

said cam ring has a slot which carries a roller associated with each of the links; and

a single slot carries a plurality of said rollers, with one said roller associated with each of the links.

19. The gas turbine engine as set forth in claim 18, wherein there is no actuator radially outward of said inlet guide vanes to provide a smaller envelope.