Method for making ceramic turbine engine article

Patent metadata

Field	Value
Publication number	US-2018135437-A1
Application number	US-201615354055-A
Country	US
Kind code	A1
Filing date	Nov 17, 2016
Priority date	Nov 17, 2016
Publication date	May 17, 2018
Grant date	—

Abstract

A method of fabricating a ceramic turbine engine article includes building a wall of the article from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the one or more sacrificial core elements to leave one or more cavities in the wall.

First claim

What is claimed is:

1 . A method of fabricating a ceramic turbine engine article, the method including building a wall of the article from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the one or more sacrificial core elements to leave one or more cavities in the wall.

2 . The method as recited in claim 1 , wherein the article is an airfoil piece that defines a portion of an airfoil profile.

3 . The method as recited in claim 2 , wherein the article is an airfoil piece that defines a leading end of an airfoil profile.

4 . The airfoil as recited in claim 2 , wherein at least one of the cavities is an internal cooling circuit in the wall.

5 . The method as recited in claim 4 , wherein the internal cooling circuit includes a circuitous passage within the wall.

6 . The method as recited in claim 4 , wherein another of the cavities is a core cavity in the airfoil piece, and the core cavity is isolated from the internal cooling circuit.

7 . The method as recited in claim 4 , wherein one of the circuitous passage includes a passage loop.

8 . The method as recited in claim 1 , wherein the sacrificial core elements are carbon elements, and the removal of the one or more sacrificial core elements includes thermally removing the carbon elements.

9 . The method as recited in claim 1 , wherein the preceramic layers are fiber layers impregnated with preceramic polymer.

10 . The method as recited in claim 1 , including arranging the preceramic layers to encompass at least one of the sacrificial core elements.

11 . The method as recited in claim 1 , wherein the wall includes a first internal rib and a second internal rib, the first internal rib including an impingement orifice that opens toward the second internal rib.

12 . The method as recited in claim 1 , wherein the wall includes inner and outer wall portions that define a passage there between, at least one of the inner or outer wall portions including a plurality of flow guides that project into the passage toward the other of the inner or outer wall portions.

13 . The method as recited in claim 1 , wherein the wall includes inner and outer wall portions that define a passage there between, at least one of the inner or outer wall portions including a plurality of flow dimples that border the passage.

14 . A method of fabricating a ceramic airfoil piece that defines a portion of an airfoil profile, the method including building an exterior wall of the ceramic airfoil piece from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the sacrificial core elements to leave an internal cooling circuit in the external wall of the ceramic airfoil piece.

15 . The method as recited in claim 14 , wherein the one or more sacrificial core elements are carbon elements, and the removal of the one or more sacrificial core elements includes thermally removing the carbon elements.

16 . The method as recited in claim 14 , wherein the preceramic layers are fiber layers impregnated with preceramic polymer.

17 . The method as recited in claim 14 , wherein the internal cooling circuit includes a circuitous passage within the exterior wall.

18 . The method as recited in claim 14 , wherein the ceramic airfoil piece defines a leading end of the airfoil profile.

Assignees

• United Technologies Corp

Inventors

• Propheter-Hinckley Tracy A
• Mccaffrey Michael G
• Surace Raymond
• Devore Matthew A

Classifications

• B23P15/04

  turbine or like blades from several pieces · CPC title

• F01D25/12

  Cooling · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2230/60

  Assembly methods · CPC title