Gas Turbine Engine Systems Involving Gear-Driven Variable Vanes

• US 20090104022A1
• Filed: 10/22/2007
• Published: 04/23/2009
• Est. Priority Date: 10/22/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: McCaffrey, Michael G., Suljak, George T. JR.
• Granted Patent: US 8,240,983 B2
• Time in Patent Office: Days
• 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
• CPC Class Codes: F05D 2270/66 Mechanical actuators F05D2270/62 takes precedence

Abstract

Gas turbine engine systems involving gear-driven variable vanes are provided. In this regard, a representative gas turbine engine system includes: a ring gear assembly operative to be mounted within an engine casing; and a vane module having a first vane airfoil and a first gear, the first gear being operative to engage the ring gear assembly such that movement of the ring gear alters a position of the first vane airfoil.

Claims

1. A gas turbine engine system comprising:

a ring gear assembly operative to be mounted within an engine casing; and

a vane module having a first vane airfoil and a first gear, the first gear being operative to engage the ring gear assembly such that movement of the ring gear alters a position of the first vane airfoil.

2. The system of claim 1, further comprising a mounting assembly defining an annular track along which the ring gear assembly is carried.

3. The system of claim 1, wherein the ring gear assembly comprises a first ring gear and a second ring gear, the first ring gear and the second ring gear having opposing gear teeth operative to engage the first gear of the vane module therebetween.

4. The system of claim 3, wherein:

the mounting assembly exhibits a split-ring configuration having a forward annular member and an aft annular member; and

the forward member and the aft member engage each other to mount the vane module.

5. The system of claim 1, wherein:

the vane module further comprises an inner platform and an outer platform, the first vane airfoil extending between the inner platform and the outer platform; and

the vane module is operative to rotate the first vane airfoil relative to the inner platform and the outer platform, responsive to rotation of the first gear.

6. The system of claim 5, wherein the vane module further comprises a second vane airfoil extending between the inner platform and the outer platform such that the first vane airfoil rotates relative to the second vane airfoil, the inner platform and the outer platform, responsive to rotation of the first gear.

7. The system of claim 1, further comprising:

a motor;

a shaft extending from the motor; and

a drive gear attached to the shaft and being operative to engage the ring gear assembly.

8. The system of claim 1, further comprising a compression mechanism operative to urge the ring gear assembly into engagement with the first gear of the vane module.

9. The system of claim 1, wherein:

the ring gear assembly comprises a first ring gear and a second ring gear;

the first ring gear is operative to move circumferentially with respect to the second ring gear.

10. The system of claim 1, wherein:

the mounting assembly exhibits a split-ring configuration having a forward annular member and an aft annular member;

the forward annular member has a split aperture and the aft annular member has a corresponding split aperture; and

a portion of the vane module is captured between the split aperture and the corresponding split aperture.

11. A gas turbine engine comprising:

a compressor;

a combustion section operative to receive compressed air from the compressor;

a turbine operative to drive the compressor;

a casing operative to encase the turbine; and

a gear-driven variable vane system having a ring gear assembly and a vane module, the ring gear assembly being mounted within an interior of the casing, the vane module having a first vane airfoil and a first gear, the first gear being operative to engage the ring gear assembly such that movement of the ring gear alters a position of the first vane airfoil.

12. The engine of claim 11, wherein the ring gear assembly comprises a first ring gear and a second ring gear, the first ring gear and the second ring gear having opposing gear teeth operative to engage the first gear of the vane module therebetween.

13. The engine of claim 11, wherein:

the vane module is a first vane module of a vane assembly having multiple vane modules; and

the vane modules are annularly positioned about a longitudinal axis of the engine.

14. The engine of claim 11, further comprising a mounting assembly located within the interior of the casing and defining an annular track along which the ring gear assembly is carried.

15. The engine of claim 14, wherein:

the mounting assembly exhibits a split-ring configuration having a forward annular member and an aft annular member; and

the forward member and the aft member engage each other to mount the vane module.

16. The system of claim 11, further comprising:

a motor located outside of the casing;

a shaft extending from the motor and into the casing; and

a drive gear attached to the shaft and positioned in the interior of the casing, the drive gear being operative to engage the ring gear assembly.

17. The engine of claim 11, wherein:

the mounting assembly exhibits a split-ring configuration having a forward annular member and an aft annular member;

the forward annular member has a split aperture and the aft annular member has a corresponding split aperture; and

a portion of the vane module is captured between the split aperture and the corresponding split aperture.

18. A vane module for a gas turbine engine comprising:

an inner platform, an outer platform, a first vane airfoil and a first gear, the first vane airfoil extending between the inner platform and the outer platform, the vane module being operative to rotate the first vane airfoil relative to the inner platform and the outer platform, responsive to rotation of the first gear.

19. The vane module of claim 18, further comprising a second vane airfoil extending between the inner platform and the outer platform

20. The vane module of claim 19, wherein the vane module is operative to rotate the first vane airfoil relative to the second vane airfoil, the inner platform and the outer platform, responsive to rotation of the first gear.