Gas turbine engine systems involving mechanically alterable vane throat areas

• US 8,052,388 B2
• Filed: 11/29/2007
• Issued: 11/08/2011
• Est. Priority Date: 11/29/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: McCaffrey, Michael G, Sabatino, Daniel R, Magge, Shankar S, Burge, Joseph Clayton, Wagner, Joel H
• Primary Examiner(s): Kershteyn; Igor
• Application Number:
  US11/947,160
• Publication Number:
  US 20090142181A1
• Time in Patent Office: 1,440 Days
• Field of Search: 415/115, 415/119, 416/23, 416/24, 416/36, 416/42, 416/61, 416/97.R, 416/DIG.5
• US Class Current: 416/23
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 9/02 Nozzles; Nozzle boxes; Stator blades; Guide conduits , e.g. individual nozzles nozzle boxes F01D9/047
• CPC Class Codes: F05D 2270/17 to control boundary layer

Abstract

Gas turbine engine systems involving mechanically alterable vane throat areas are provided. In this regard, a representative vane for a gas turbine engine includes: a leading edge; a trailing edge; a suction side surface extending between the leading edge and the trailing edge; a cavity having an aperture located in the suction side surface; and a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture.

Claims

1. A vane for a gas turbine engine comprising:

a leading edge;

a trailing edge;

a suction side surface extending between the leading edge and the trailing edge;

a cavity having an aperture located in the suction side surface;

a barrel located within the cavity and being moveable therein such that movement of the barrel alters an extent to which the barrel protrudes through the aperture; and

a fluidic jet having an outlet port operative to emit gas into a gas flow path located adjacent to the suction side surface.

2. The vane of claim 1, wherein the outlet port of the fluidic jet is positioned upstream of the barrel.

3. The vane of claim 1, wherein the outlet port of the fluidic jet is moveable with the barrel.

4. The vane of claim 3, wherein the outlet port is a first of multiple outlet ports moveable with the barrel.

5. The vane of claim 4, wherein at least two of the outlet ports are located at different radial positions with respect to a rotational axis of the barrel.

6. The vane of claim 1, wherein the barrel is rotatable through a range of positions, with a first of the positions corresponding to a portion of the exterior surface of the barrel being flush with the suction side surface.

7. The vane of claim 6, wherein a second of the positions corresponds to the portion of the exterior surface of the barrel protruding from the aperture.

8. The vane of claim 6, wherein:

the barrel mounts an outlet port of a fluidic jet;

in a second position, the outlet port is not positioned to emit gas into a gas flow path located adjacent to the suction side surface; and

in a third of the positions, the outlet port is positioned to emit gas into the gas flow path.

9. The vane of claim 1, wherein:

the vane further comprises a plenum pneumatically communicating with the cavity;

the barrel has a channel extending between an inlet and an outlet, the barrel being selectively moveable between a first position, in which the inlet is aligned with the plenum such that gas from the plenum is directed through the channel and out of the outlet and, a second position, in which the inlet is not aligned with the plenum.

10. The vane of claim 1, wherein the vane is a stationary vane.

11. A vane assembly for a gas turbine engine comprising:

a vane having a pressure side; and

an adjacent vane having a suction side located adjacent to the pressure side, the vane and the adjacent vane defining a throat area therebetween, the suction side of the adjacent vane having a cavity and a barrel retained by the cavity, the barrel being moveable such that movement of the barrel alters the throat area.

12. The vane assembly of claim 11, wherein:

the barrel is a first barrel; and

the vane has a suction side and a second barrel located adjacent to the suction side of the vane.

13. The vane assembly of claim 11, further comprising a fluidic jet having an outlet port operative to emit gas into a gas flow path located between the vane and the adjacent vane.

14. The vane assembly of claim 11, wherein a fluidic jet is operative to alter the throat area.

15. The vane assembly of claim 11, wherein a fluidic jet is.

16. The vane assembly of claim 11, wherein a barrel is a rotatable barrel operative to rotate about a rotational axis.

17. The vane assembly of claim 11, wherein the barrel lacks rotational symmetry.

18. A gas turbine engine comprising:

a vane assembly having a vane and an adjacent vane;

the vane having a pressure side; and

the adjacent vane having a suction side located adjacent to the pressure side, the vane and the adjacent vane defining a throat area therebetween, the suction side of the adjacent vane having a cavity and a barrel retained by the cavity, the barrel being moveable such that movement of the barrel alters the throat area.

19. The engine of claim 18, wherein the engine is a turbofan gas turbine engine.

20. The engine of claim 18, wherein the vane assembly is a high pressure turbine vane assembly.