Composite airfoil assembly

Patent metadata

Field	Value
Publication number	US-8967974-B2
Application number	US-201213342599-A
Country	US
Kind code	B2
Filing date	Jan 3, 2012
Priority date	Jan 3, 2012
Publication date	Mar 3, 2015
Grant date	Mar 3, 2015

Abstract

A composite blade assembly for mounting on a turbine wheel includes a ceramic airfoil and an airfoil platform. The ceramic airfoil is formed with an airfoil portion, a blade shank portion and a blade dovetail tang. The metal platform includes a platform shank and a radially inner platform dovetail. The ceramic airfoil is captured within the metal platform, such that in use, the ceramic airfoil is held within the turbine wheel independent of the metal platform.

First claim

What is claimed is:

1. A composite blade assembly for mounting in a slot provided on a turbine wheel, the composite blade assembly comprising:
a ceramic airfoil formed with an airfoil portion, an airfoil shank portion and an airfoil dovetail tang, wherein the airfoil dovetail tang includes a leading edge, a trailing edge, and a radially inward surface extending between the leading edge and the trailing edge; and
a metal platform having a platform shank, a platform shank cavity and a radially inner platform dovetail, wherein a length of the radially inner platform dovetail is radially inward of and borders the radially inward surface of the dovetail tang;
said ceramic airfoil dovetail tang captured within said metal platform shank cavity, such that in use, said ceramic airfoil is held within the slot in the turbine wheel independent of said metal platform.

2. The composite blade assembly of claim 1 wherein said airfoil portion projects through an opening in a radially outer surface of said metal platform.

3. The composite blade assembly of claim 2 wherein said radially inner platform dovetail includes at least one dovetail tang, said at least one dovetail tang formed with a partial cut-out between opposite ends thereof.

4. The composite blade assembly of claim 3 wherein said partial cut out is substantially centered between said opposite ends.

5. The composite blade assembly of claim 4 wherein said blade dovetail tang forms a continuation of said at least one platform dovetail tang.

6. The composite blade assembly of claim 1 wherein said ceramic airfoil is comprised of a CMC composite material.

7. The composite airfoil assembly of claim 1 wherein said ceramic airfoil is comprised of a silicon matrix fiber material.

8. The composite airfoil assembly of claim 1 wherein said ceramic airfoil is comprised of a silicon nitride or a monolithic ceramic material.

9. A turbine rotor wheel comprised of:
a plurality of composite blade assemblies, each blade assembly comprising a ceramic airfoil and a metal platform, the ceramic airfoil includes a ceramic dovetail tang comprising a leading edge, a trailing edge and a radially inward surface extending between the leading edge and the trailing edge, and
the metal platform including a platform shank and a radially inner platform dovetail, wherein the radially inner platform dovetail includes a length of a dovetail portion radially inward of and bordering the radially inward surface of the dovetail tang; and
said ceramic airfoil dovetail tang is captured within said metal platform.

10. The turbine rotor wheel of claim 9 wherein said radially inner platform dovetail is formed with a partial cut-out to receive said ceramic airfoil dovetail tang.

11. The turbine rotor wheel of claim 10 wherein said radially inner platform dovetail includes at least one dovetail tang, said at least one dovetail tang formed with said partial cut-out.

12. The turbine rotor wheel of claim 11 wherein said partial cut out is substantially centered between opposite ends of said at least one dovetail tang.

13. The turbine rotor wheel of claim 12 wherein said ceramic airfoil dovetail tang is aligned along an axial direction with said at least one dovetail tang of the radially inner platform.

14. The turbine rotor wheel of claim 9 wherein said ceramic airfoil is comprised of a CMC composite material.

15. The turbine rotor wheel of claim 9 wherein said radially inner platform dovetail includes at least three dovetail tangs, a radially outer one of said at least three dovetail tangs formed with said partial cut-out; and said radially inner dovetail tang of said ceramic airfoil forms a continuation of said radially outer one of said at least three dovetail tangs.

16. The turbine rotor wheel of claim 9 wherein said ceramic airfoil is comprised of a silicon nitride or monolithic ceramic material.

17. A method of assembling a ceramic airfoil to a metal platform comprising:
a. providing a ceramic airfoil with an airfoil portion, a shank portion and a radially inner dovetail tang; and
b. casting a metal platform about the shank portion and the radially inner dovetail tang of the ceramic airfoil, wherein the casting includes casting a length of the radially inner dovetail tang to be radially inward of and boarding a radially inward surface of the radially inner dovetail tang of the ceramic airfoil.

18. The method of claim 17 wherein said metal platform is formed with a platform shank and a radially inner platform dovetail; said ceramic airfoil portion projecting through an opening in a radially outer surface of said metal platform.

19. The method of claim 18 wherein said radially inner portion dovetail includes a dovetail tang with a center section cutout, and wherein said radially inner dovetail tang of said ceramic airfoil is received within said center section cutout.

20. The method of claim 19 including maintaining, in use, a clearance between a radially inner surface of said radially inner dovetail tang of said ceramic airfoil and an outer surface of said radially inner dovetail tang of said radially inner platform dovetail.

Assignees

• Garcia-Crespo Andres Jose
• Gen Electric

Inventors

• Garcia-Crespo Andres Jose

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F01D11/008

  by spacer elements between the blades, e.g. independent interblade platforms · CPC title

• F01D5/147

  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 title