Cmc blade with monolithic ceramic platform and dovetail

Patent metadata

Field	Value
Publication number	US-2016222802-A1
Application number	US-201415025949-A
Country	US
Kind code	A1
Filing date	Sep 17, 2014
Priority date	Oct 11, 2013
Publication date	Aug 4, 2016
Grant date	—

Abstract

A blade for a gas turbine engine includes a fiber reinforced ceramic matrix composite structure that provides an airfoil with an exposed exterior airfoil surface and a refractory structure that provides at least an outer portion of a root secured relative to the airfoil.

First claim

What is claimed is:

1 . A blade for a gas turbine engine comprising:
a fiber reinforced ceramic matrix composite structure providing an airfoil with an exposed exterior airfoil surface; and a refractory structure providing at least an outer portion of a root secured relative to the airfoil.

2 . The blade according to claim 1 , wherein the ceramic matrix composite structure includes an inner root, and the outer portion of the root is secured over the inner root, the refractory structure including substantially isotropic, monolithic refractory material including but not limited to silicon nitride, silicon carbide, aluminum nitride, molybdenum silicide, molybdenum-silicon-boron alloy, and admixtures thereof.

3 . The blade according to claim 2 , wherein the outer portion includes angled walls that provide a dovetail.

4 . The blade according to claim 3 , wherein the inner root includes a root end that extends beyond the angled walls.

5 . The blade according to claim 1 , wherein the refractory structure includes a platform.

6 . The blade according to claim 5 , wherein the refractory structure has a neck interconnecting the outer portion to the platform.

7 . The blade according to claim 5 , wherein the platform includes an aperture through which the airfoil extends.

8 . The blade according to claim 7 , wherein the platform surrounds a perimeter of airfoil.

9 . The blade according to claim 5 , wherein the ceramic matrix composite structure provides a fillet arranged about the perimeter and overlapping the platform and the airfoil.

10 . The blade according to claim 5 , wherein the refractory structure includes an integral fillet arranged about the perimeter.

11 . A rotating assembly for a gas turbine engine comprising:
a rotor including a slot; and a blade having a fiber reinforced ceramic matrix composite structure that provides an airfoil with an exposed exterior airfoil surface, and a refractory structure providing at least an outer portion of a root secured relative to the airfoil and received in the slot.

12 . The rotating assembly according to claim 11 , wherein the ceramic matrix composite structure includes an inner root, and the outer portion is secured over the inner root, the refractory structure including substantially isotropic, monolithic refractory material including but not limited to silicon nitride, silicon carbide, aluminum nitride, molybdenum silicide, molybdenum-silicon-boron alloy, and admixtures thereof.

13 . The rotating assembly according to claim 12 , wherein the outer portion includes angled walls that provide a dovetail, the dovetail engaging the rotor within the slot.

14 . The rotating assembly according to claim 13 , wherein the inner root includes a root end that extends beyond the angled walls.

15 . The rotating assembly according to claim 14 , wherein the refractory structure includes a platform extending circumferentially to opposing mate faces, the mate face arranged proximate to adjacent mate faces of adjacent blades supported by the rotor.

16 . The rotating assembly according to claim 15 , wherein the refractory structure has a neck interconnecting the outer portion to the platform.

17 . The rotating assembly according to claim 15 , wherein the platform includes an aperture through which the airfoil extends.

18 . The rotating assembly according to claim 17 , wherein the platform surrounds a perimeter of airfoil.

19 . The rotating assembly according to claim 15 , wherein the ceramic matrix composite structure provides a fillet arranged about the perimeter and overlapping the platform and the airfoil.

20 . The rotating assembly according to claim 15 , wherein the refractory structure includes an integral fillet arranged about the perimeter.

Assignees

• United Technologies Corp

Inventors

• Holowczak John E
• Mccaffrey Michael G

Classifications

• 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

• F05D2240/80

  Platforms for stationary or moving blades · CPC title

• F01D5/30

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title