3D contoured vane endwall for variable area turbine vane arrangement

• US 8,105,019 B2
• Filed: 12/10/2007
• Issued: 01/31/2012
• Est. Priority Date: 12/10/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: McCaffrey, Michael G., Hudson, Eric A., Hill, James D., Magge, Shankar S., Wagner, Joel H.
• Primary Examiner(s): EDGAR, RICHARD A
• Application Number:
  US11/953,478
• Publication Number:
  US 20090148282A1
• Time in Patent Office: 1,513 Days
• Field of Search: 415/161, 415/160, 415/159
• 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: F02C 9/22 by adjusting turbine vanes

Abstract

A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing.

Claims

1. A turbine nozzle segment for a gas turbine engine comprising:

an arcuate vane platform segment having a substantially flat surface;

a rotational turbine vane rotatable about an axis of rotation over said substantially flat surface; and

a contour adjacent said arcuate vane platform segment to define a faceted flowpath surface.

2. The turbine nozzle segment as recited in claim 1, wherein said faceted flowpath surface minimizes flow disturbances from said substantially flat surface.

3. The turbine nozzle segment as recited in claim 1, further comprising a seal plate movable relative to a vane endwall of said rotational turbine vane segment generally parallel to said axis of rotation.

4. The turbine nozzle segment as recited in claim 3, wherein said seal plate contacts said substantially flat surface.

5. The turbine nozzle segment as recited in claim 3, wherein said seal plate is pressure loaded toward said substantially flat surface.

6. The turbine nozzle segment as recited in claim 3, wherein said seal plate is mechanically loaded toward said substantially flat surface.

7. The turbine nozzle segment as recited in claim 1, wherein said substantially flat surface is airfoil shaped.

8. The turbine nozzle segment as recited in claim 1, wherein said rotational turbine vane comprises a fixed airfoil portion and a pivoting airfoil portion which pivots relative to said fixed airfoil portion, said pivoting airfoil portion adjacent said substantially flat surface.

9. The turbine nozzle segment as recited in claim 8, wherein said substantially flat surface is airfoil shaped to correspond with said pivoting airfoil portion.

10. The turbine nozzle segment as recited in claim 1, wherein said arcuate vane platform is an inner arcuate vane platform.

11. The turbine nozzle segment as recited in claim 1, wherein said arcuate vane platform is an outer arcuate vane platform.

12. The turbine nozzle segment as recited in claim 1, wherein said substantially flat surface is recessed relative said arcuate vane platform segment.

13. The turbine nozzle segment as recited in claim 1, wherein said substantially at surface is raised relative said arcuate vane platform segment.

14. A method of varying a turbine nozzle throat area of a gas turbine engine comprising:

locating a rotational turbine vane adjacent to a substantially flat surface between a first fixed turbine vane and a second fixed turbine vane;

locating contours adjacent the substantially flat surface to define a faceted surface which minimizes flow disturbances from the substantially flat surface; and

rotating the rotational turbine vane about an axis of rotation over said substantially flat surface to vary a throat area concurrently between the rotational stator vane and both the first fixed turbine vane and the second fixed turbine vane.

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

pressurizing a seal plate relative to an endwall of said rotational turbine vane to maintain contact with said substantially flat surface.

16. A method as recited in claim 14, further comprises:

rotating a pivoting segment of the rotational turbine vane about an axis of rotation.

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

selectively covering and uncovering cooling apertures through the substantially flat surface in response to rotation of the rotating turbine vane.

18. A turbine nozzle segment for a gas turbine engine comprising:

an arcuate vane platform segment having a substantially flat surface; and

a rotational turbine vane rotatable about an axis of rotation over said substantially flat surface; and

a contour adjacent said arcuate vane platform segment to define a faceted flowpath surface.

19. The turbine nozzle segment as recited in claim 18, wherein said substantially flat surface is contoured to a range of motion of said rotational turbine vane.

20. The turbine nozzle segment as recited in claim 18, wherein said arcuate vane platform is an inner arcuate vane platform.