Turbine airfoil with trailing edge

• US 8,070,454 B1
• Filed: 12/12/2007
• Issued: 12/06/2011
• Est. Priority Date: 12/12/2007
• Status: Active Grant

• Current Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Original Assignee: Florida Turbine Technologies, Inc. (Kratos Defense & Security Solutions Incorporated)
• Inventors: Rawlings, Christopher K.
• Primary Examiner(s): Nguyen, Ninh H
• Application Number:
  US12/001,514
• Time in Patent Office: 1,455 Days
• Field of Search: 416/241.R, 416/241.A, 416/228
• US Class Current: 416/241.R
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F05B 2230/90 Coating; Surface treatment manufacture with deposition of material F05B2220/30
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment manufacture with deposition of material F05D2230/30

Abstract

A turbine airfoil with a relatively thick TBC applied over the airfoil surface. The airfoil has a surface contour on the trailing edge region with a forward end having a large amount of taper and a rearward end with less taper such that a substantially constant wall thickness is formed in the rearward end. The TBC is applied over the airfoil surface and tapers off at the trailing edge ends on the pressure side and the suction side walls to produce an ideal surface contour on the airfoil. In another embodiment, the airfoil surface includes a tapered section at the trailing edge region, and the TBC is applied over the taper so that an over-coating is formed. The TBC over-coating is then removed and a smooth and ideal surface contour is produced along the airfoil surface. Small raised bumps each having a height of the desired thickness of the TBC to be applied over the respective bump is used to control the finished thickness of the TBC.

Claims

1. A turbine airfoil for use in a gas turbine engine, the turbine airfoil comprising:

a leading edge and a trailing edge;

a pressure side wall and a suction side wall;

the trailing edge region of the airfoil having a discontinuous taper angle such that when a TBC is applied to the airfoil an ideal surface contour is formed;

the discontinuous taper angle includes a first tapered section and a second tapered section located aft of the first tapered section, the second tapered section having less taper than the first tapered section; and

,

the second tapered section produces a substantially constant airfoil wall thickness.

2. The turbine airfoil of claim 1, and further comprising:

the TBC is a relatively thick TBC such that tapering off of the TBC at the trailing edge would produce an unacceptable aerodynamic surface contour on a prior art airfoil contour.

3. A turbine airfoil for use in a gas turbine engine, the turbine airfoil comprising:

a leading edge and a trailing edge;

a pressure side wall and a suction side wall;

the trailing edge region of the airfoil having a discontinuous taper angle such that when a TBC is applied to the airfoil an ideal surface contour is formed; and

,

a TBC applied over the airfoil surface, the TBC on the pressure side wall tapering off at the trailing edge to zero thickness.

4. The turbine airfoil of claim 3, and further comprising:

the TBC extends toward the trailing edge on the pressure side and the suction side walls of the airfoil, and the TBC tapers off to zero thickness substantially at the trailing edge of the airfoil on both sides.

5. A turbine airfoil for use in a gas turbine engine, the turbine airfoil comprising:

a leading edge and a trailing edge;

a pressure side wall and a suction side wall;

the trailing edge region of the airfoil having a discontinuous taper angle such that when a TBC is applied to the airfoil an ideal surface contour is formed; and

,

a plurality of local bumps extending out from the airfoil surface, each bump having a height substantially equal to the desired thickness of the TBC to be applied around the particular bump.

6. A turbine airfoil for use in a gas turbine engine, the turbine airfoil comprising:

a leading edge and a trailing edge;

a pressure side wall and a suction side wall;

a local increase in the airfoil thickness on the pressure side to accommodate strip masking; and

,

a TBC applied over the airfoil surface and ending at the local increase thickness.

7. The turbine airfoil of claim 6, and further comprising:

the local increase is formed on both the pressure side and the suction side walls.

8. The turbine airfoil of claim 7, and further comprising:

the airfoil outer surface is decreased in thickness from the pressure side local increase, around the leading edge of the airfoil, and ending at the local increase on the suction side such that a relatively thick TBC applied over the decreased airfoil thickness sections will produce an ideal surface contour.

9. The turbine airfoil of claim 8, and further comprising:

a TBC over the airfoil surface and extending from the local thickness increase from the pressure side around the leading edge and to the local thickness increase on the suction side such that a smooth transition from the TBC to the trailing edge airfoil surface is formed.

10. The turbine airfoil of claim 6, and further comprising:

the local increase is a tapered section.

11. The turbine airfoil of claim 6, and further comprising:

the local increase is located in the airfoil trailing edge region.

12. A process of forming a turbine airfoil with a TBC applied over the airfoil surface, comprising the steps of:

forming the airfoil surface with a contour having a local increase in airfoil thickness on the trailing edge region of the pressure side of the airfoil;

forming the airfoil surface with a reduced contour from the pressure side local increase in thickness to at least the leading edge of the airfoil;

applying a TBC to the airfoil surface and past the local increase in thickness such that an over-coating of the TBC is formed; and

,

removing the over-coated TBC such that a smooth surface contour is produced along the pressure side surface of the airfoil.

13. The process of forming the turbine airfoil of claim 12, and further providing the steps of:

forming a local increase in thickness on the suction side of the airfoil;

applying the TBC to the airfoil surface and past the local increase in thickness on the suction side such that an over-coating of the TBC is formed; and

,

removing the over-coated TBC on the suction side such that a smooth surface contour is produced along the suction side surface of the airfoil.

14. The process of forming the turbine airfoil of claim 13, and further providing the step of:

forming the airfoil surface with a reduced contour from the pressure side local increase in thickness, around the leading edge and to the local increase in thickness on the suction side.

15. The process of forming the turbine airfoil of claim 12, and further providing the steps of:

forming raised bumps on the airfoil surface; and

,

removing the TBC until the raised bumps are exposed.

16. A turbine airfoil for use in a gas turbine engine, the turbine airfoil comprising:

a leading edge and a trailing edge;

a pressure side wall and a suction side wall;

a positive taper on the pressure side wall and the suction side wall at a beginning of a trailing edge region of the airfoil;

a TBC applied over the airfoil and ending at the two positive tapers; and

,

the trailing edge region on the pressure side wall and the suction side wall is uncovered by a TBC.

17. The turbine airfoil of claim 16, and further comprising:

the positive taper on the pressure side wall is aft of the positive taper on the suction side wall.

18. The turbine airfoil of claim 16, and further comprising:

the TBC ending at the positive tapers is flush with the uncovered pressure and suction side walls of the trailing edge region.

19. The turbine airfoil of claim 18, and further comprising:

the discontinuous surfaces are formed by a positive taper.

20. A turbine airfoil for use in a gas turbine engine, the turbine airfoil comprising:

a leading edge region and a trailing edge region;

a pressure side wall and a suction side wall extending between the leading edge region and the trailing edge region;

a discontinuous surface formed between the pressure side and suction side walls and the trailing edge region;

the trailing edge region is not covered with a TBC; and

,

the pressure side and suction side walls are covered with a TBC with a smooth surface transition between the TBC covered walls and the uncovered walls of the airfoil.