Gas turbine engine component with platform cooling circuit

Patent metadata

Field	Value
Publication number	US-10041374-B2
Application number	US-201514665182-A
Country	US
Kind code	B2
Filing date	Mar 23, 2015
Priority date	Apr 4, 2014
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

A component according to an exemplary aspect of the present disclosure includes, among other things, a platform and a feed cavity that feeds a cooling fluid inside of the platform. The feed cavity includes a leg portion and a main body portion that extends from the leg portion inside of the platform. A cooling cavity is inside the platform and in fluid communication with the feed cavity.

First claim

What is claimed is:

1. A casting system, comprising:
a core assembly configured to form a platform cooling circuit, said core assembly including a feed core that includes a leg portion and a main body portion that extends from said leg portion; and
a shell that surrounds said core assembly, wherein said leg portion extends into said shell and said main body portion is spaced from said shell, wherein said leg portion is adjustable within said shell.

2. The casting system as recited in claim 1 , wherein said core assembly includes a second core that is separate from said feed core.

3. The casting system as recited in claim 2 , wherein said core assembly comprises an inlet that plugs into said feed core and an outlet that extends into said shell.

4. The casting system as recited in claim 3 , wherein said inlet is received within a recess of said main body portion of said feed core.

5. The casting system as recited in claim 3 , wherein said outlet extends from said second core to said shell.

6. The casting system as recited in claim 1 , wherein said feed core includes a second leg portion extending into said shell.

7. A casting system, comprising:
a core assembly configured to form a platform cooling circuit, said core assembly including a feed core that includes a lea portion and a main body portion that extends from said leg portion; and
a shell that surrounds said core assembly, wherein said leg portion extends into said shell and said main body portion is spaced from said shell, wherein said feed core is adjustable by moving said feed core relative to said shell.

8. The casting system as recited in claim 7 , said core assembly comprising
an inlet that plugs into said feed core and an outlet that extends into said shell,
a second core that is separate from said feed core, wherein said inlet extends from said second core and is received in a recess in said feed core.

9. The casting system as recited in claim 8 , wherein ceramic glue or adhesive fills a gap between said inlet and said recess to allow for small relative movements between said feed core and said second core.

10. The casting system as recited in claim 8 , wherein the second core includes a plurality of grooves for a plurality of heat augmentation devices.

11. A method of casting a gas turbine engine component, comprising:
providing a shell having a casting area;
providing a core assembly within said casting area, such that a leg portion of said core assembly extends into said shell, and a main body portion extending from said leg portion is within said casting area;
communicating molten material into said casting area, and
vertically adjusting said leg portion relative to said shell before said communicating.

12. The method as recited in claim 11 , wherein said providing said core assembly includes:
providing a second core separate from said main body portion;
inserting an inlet extending from said second core into a recess of said main body portion; and
providing an outlet that extends from said second core into said shell.

Assignees

• United Technologies Corp

Inventors

• Spangler Brandon W
• Vu Ky H
• Cavallo Gina

Classifications

• B22C9/103

  Multipart cores · CPC title

• F01D5/18

  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 title

• F01D5/081 Primary

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F01D5/186

  Film cooling (F01D5/187 takes precedence) · CPC title

• F01D5/181

  Blades having a closed internal cavity containing a cooling medium, e.g. sodium · CPC title