Turbine Airfoil With Additive Manufactured Reinforcement of Thermoplastic Body

Patent metadata

Field	Value
Publication number	US-2016333733-A1
Application number	US-201515107591-A
Country	US
Kind code	A1
Filing date	Jan 9, 2015
Priority date	Jan 30, 2014
Publication date	Nov 17, 2016
Grant date	—

Abstract

A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed.

First claim

1 . A component for a gas turbine engine comprising:
an airfoil body formed of a plastic; and a reinforcement portion, said reinforcement portion having webs formed of a metallic material and extending into said airfoil.

2 . The component for a gas turbine engine as set forth in claim 1 , wherein said webs are buried within the plastic of said body at said airfoil.

3 . The component for a gas turbine engine as set forth in claim 1 , wherein said body having a passage and a shaft on said reinforcement portion extending through said passage.

4 . The component for a gas turbine engine as set forth in claim 3 , wherein said shaft connects trunnions at opposed ends of said shaft.

5 . The component for a gas turbine engine as set forth in claim 1 , wherein said plastic is one of a thermoplastic or a thermoset resin.

6 . The component for a gas turbine engine as set forth in claim 4 , wherein said component is a variable vane.

7 . The component for a gas turbine engine as set forth in claim 6 , wherein said trunnions extend outwardly of said body.

8 . The component for a gas turbine engine as set forth in claim 1 , wherein said web including portions extending into said airfoil, with a radial dimension defined along said shaft, with at least some of said webs extending generally perpendicular to said radial direction, and others of said webs extending to have both an axial and a radial component, and interconnected to said at least one web extending perpendicularly to said radial component.

9 . A gas turbine engine comprising:
a compressor section and a turbine section, with a component having an airfoil included in at least one of said compressor and turbine sections; said component including an airfoil body formed of a plastic, and a reinforcement portion, said reinforcement portion having webs formed of a metallic material and extending into said airfoil.

10 . The gas turbine engine as set forth in claim 9 , wherein said webs are buried within the plastic of said body at said airfoil.

11 . The gas turbine engine as set forth in claim 9 , wherein said body having a passage and a shaft on said reinforcement portion extending through said passage.

12 . The gas turbine engine as set forth in claim 11 , wherein said shaft connects trunnions at opposed ends of said shaft.

13 . The gas turbine engine as set forth in claim 9 , wherein said plastic is one of a thermoplastic or a thermoset resin.

14 . The gas turbine engine as set forth in claim 12 , wherein said component is a variable vane.

15 . The gas turbine engine as set forth in claim 14 , wherein said trunnions extend outwardly of said body.

16 . The gas turbine engine as set forth in claim 9 , wherein said web including portions extending into said airfoil, with a radial dimension defined along said shaft, with at least some of said webs extending generally perpendicular to said radial direction, and others of said webs extending to have both an axial and a radial component, and interconnected to said at least one web extending perpendicularly to said radial component.

17 . A method of forming a component for use in a gas turbine engine comprising:
forming a reinforcement portion including webs by an additive manufacturing process; and placing said reinforcement portion into a plastic mold and placing plastic in said mold around said reinforcement portion, with said plastic forming a body including an airfoil.

18 . The method as set forth in claim 5 , wherein said molded body having a passage and said reinforcement portion having a shaft extending through said passage and connecting trunnions at opposed ends of said shaft.

19 . The method as set forth in claim 17 , wherein said webs are buried within the plastic of said body at said airfoil.

20 . The method as set forth in claim 17 , wherein said plastic is one of a thermoplastic or a thermoset resin.

Assignees

• United Technologies Corp

Inventors

• Robertson Jr Thomas J

Classifications

• F01D25/005 Primary

  Selecting particular materials · CPC title

• B22F10/20 Primary

  Direct sintering or melting · CPC title

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2300/44

  Resins · CPC title

• B33Y30/00

  Apparatus for additive manufacturing; Details thereof or accessories therefor · CPC title