Turbine vane with removable platform inserts

• US 7,488,157 B2
• Filed: 07/27/2006
• Issued: 02/10/2009
• Est. Priority Date: 07/27/2006
• Status: Expired due to Fees

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Schiavo, Anthony L., Marini, Bonnie D.
• Primary Examiner(s): EDGAR, RICHARD A
• Application Number:
  US11/494,177
• Publication Number:
  US 20080025842A1
• Time in Patent Office: 929 Days
• Field of Search: 416/193.A, 416/224, 416/62, 416/96.A, 416/196, 416/197, 416/214.A, 298/891, 415/214.A
• US Class Current: 416/193.00A
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F05D 2230/80 Repairing, retrofitting or upgrading methods
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment manufacture with deposition of material F05D2230/30
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2300/21 Oxide ceramics
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/611 Coating

Abstract

Aspects of the invention are related to a turbine vane assembly in which at least one of the platforms is equipped with one or more removable platform inserts. The inserts can be used in those areas of the platform where failures or damage has been known to occur, among other locations. If an insert becomes damaged or is destroyed during engine operation, the insert can be easily replaced, and the platform frames and the airfoil can be reused. As a result, the overall life of the vane can be extended. Further, the inserts can be made of materials that can reduce cooling requirements compared to known turbine vanes, thereby allowing cooling air to be used for other uses in the engine.

Claims

1. A turbine vane assembly comprising:

an airfoil having a first end region and a second end region;

a first platform operatively connected to the first end region of the airfoil, the first platform having a gas path face, the first platform including a first platform frame having a receptacle therein, the receptacle opening to at least the gas path face; and

an insert removably retained in the receptacle, wherein the gas path face is defined at least in part by the first platform frame and the insert, wherein a plurality of passages extend through the first platform frame and into fluid communication with the receptacle, whereby a coolant can be supplied to the insert and/or the receptacle.

2. The turbine vane assembly of claim 1 wherein the insert is made of a ceramic matrix composite.

3. The turbine vane assembly of claim 1 wherein the insert is retained in the receptacle by at least one fastener.

4. The turbine vane assembly of claim 1 wherein the insert is made of metal.

5. The turbine vane assembly of claim 1 wherein the insert and the first platform frame are made of the same material.

6. The turbine vane assembly of claim 1 wherein the insert is made of a material having a lower heat resistance than the material of the first platform frame.

7. The turbine vane assembly of claim 1 wherein at least a portion of the insert is coated with a thermal insulating material.

8. The turbine vane assembly of claim 1 wherein the insert defines a majority of the gas path face of the first platform.

9. The turbine vane assembly of claim 1 wherein the first platform frame and the airfoil are unitary.

10. The turbine vane assembly of claim 1 wherein the receptacle is configured as one of a dovetail and a keyway, and wherein the insert is contoured so as to be substantially matingly received in the receptacle, whereby the insert is retainably received in the receptacle.

11. The turbine vane assembly of claim 1 wherein the receptacle is a recess.

12. A turbine vane assembly comprising:

an airfoil having a first end region and a second end region;

a first platform operatively connected to the first end region of the airfoil, the first platform having a gas path face, the first platform including a first platform frame having at least one receptacle therein, each of the receptacles opening to at least the gas path face, and

at least one insert, each of the at least one inserts being removably retained in one of the receptacles, wherein the insert is associated entirely with the first platform and forms no portion of the airfoil, wherein the insert is made of a material having a lower heat resistance than the material of the first platform frame, wherein the gas path face is defined at least in part by the first platform frame and the at least one insert.

13. The turbine vane assembly of claim 12 further including a second platform operatively connected to the second end region of the airfoil, the second platform having a gas path face, wherein the second platform includes a second platform frame having at least one receptacle therein, each of the receptacles opening to at least the gas path face, and further including at least one insert, each of the at least one inserts being removably retained in each of the receptacles, wherein the gas path face of the second platform is defined at least in part by the second platform frame and the at least one insert.

14. The turbine vane assembly of claim 13 wherein the first platform has a first quantity of inserts and the second platform has a second quantity of inserts, wherein the first and second quantities are different.

15. The turbine vane assembly of claim 13 wherein the inserts of the first platform are made of a first material, and the inserts of the second platform are made of a second material, wherein the first and second materials are different.

16. The turbine vane assembly of claim 13 wherein at least a portion of at least one of the inserts is coated with a thermal insulating material.

17. The turbine vane assembly of claim 13 wherein the at least one insert defines a majority of the gas path face of the first platform.

18. The turbine vane assembly of claim 13 wherein the first and second platform frames are unitary with the airfoil.

19. The turbine vane assembly of claim 13 wherein an image of the at least one insert of the first platform projected onto the gas path face of the second platform at least partially overlaps those portions of the gas path face defined by the at least one insert of the second platform.

20. A method of repairing a damaged turbine vane comprising the steps of:

(a) providing a turbine vane assembly that includes;

an airfoil having a first end region and a second end region;

a first platform operatively connected to the first end region of the airfoil, the first platform having a gas path face, the first platform including a first platform frame having a receptacle therein, the receptacle opening to at least the gas path face; and

an insert removably retained in the receptacle, wherein the gas path face is defined at least in part by the first platform frame and the insert, wherein the insert is associated entirely with the first platform and forms no portion of the airfoil, wherein the insert is damaged;

(b) removing the damaged insert; and

(c) placing an undamaged insert into the receptacle so that the undamaged insert is retained therein.

21. A turbine vane assembly comprising:

an airfoil having a first end region and a second end region;

a first platform operatively connected to the first end region of the airfoil, the first platform having a gas path face and an associated thickness, the first platform having a first circumferential side and a second circumferential side, the first platform including a first platform frame having a recess therein, the recess opening to the gas path face and one of the circumferential sides, wherein the recess does not extend through the entire thickness of the first platform; and

an insert being received and removably retained in the receptacle, wherein the gas path face is partially defined by the insert and wherein one of the circumferential sides is partially defined by the insert, wherein the insert is associated entirely with the first platform and forms no portion of the airfoil, whereby the insert is inserted and removed from the recess through the recess opening in the circumferential side of the first platform.