Turbine airfoil cooling system with leading edge impingement cooling system turbine blade investment casting using film hole protrusions for integral wall thickness control

Patent metadata

Field	Value
Publication number	US-10022790-B2
Application number	US-201415307073-A
Country	US
Kind code	B2
Filing date	Jun 18, 2014
Priority date	Jun 18, 2014
Publication date	Jul 17, 2018
Grant date	Jul 17, 2018

Abstract

A method of forming an airfoil ( 12 ), including: abutting end faces ( 72 ) of cantilevered film hole protrusions ( 64 ) extending from a ceramic core ( 50 ) against an inner surface ( 80 ) of a wax die ( 68 ) to hold the ceramic core in a fixed positional relationship with the wax die; casting an airfoil including a superalloy around the ceramic core; and machining film cooling holes ( 34 ) in the airfoil after the casting step to form an pattern of film cooling holes comprising the film cooling holes formed by the machining step and the cast film cooling holes ( 102 ) formed by the film hole protrusions during the casting step.

First claim

The invention claimed is:

1. A method of forming an airfoil, comprising:
forming film hole protrusions on a ceramic core at locations that correspond to locations of select film cooling holes within a pattern of film cooling holes on an airfoil formed by the ceramic core;
using the film hole protrusions to hold the ceramic core in a fixed positional relationship with a wax die while forming a wax pattern around the ceramic core;
removing the wax die;
forming a ceramic shell that surrounds the wax pattern and contacts surfaces of the film hole protrusions;
removing the wax pattern;
using the film hole protrusions to hold the ceramic core in a fixed positional relationship with the ceramic shell while casting the airfoil around the ceramic core; and
machining film cooling holes in the airfoil after the casting step to form the pattern of film cooling holes comprising the film cooling holes formed by the machining step and separate cast film cooling holes formed by the film hole protrusions during the casting step.

2. The method of claim 1 , wherein each of the film hole protrusions comprises an enlarged end face, each end face configured to rest on and flush with an inner surface of the wax die.

3. The method of claim 1 , wherein each of the film hole protrusions is fixed to the ceramic core in a manner effective to resist a bending moment of the film hole protrusion with respect to the ceramic core resulting from a force imparted to a laterally offset end face of the respective film hole protrusion.

4. The method of claim 1 , further comprising integrally casting the film hole protrusions as part of the ceramic core.

5. The method of claim 1 , further comprising forming the film hole protrusions on the ceramic core by assembling discrete film hole protrusion bodies into a partly sintered ceramic core.

6. The method of claim 5 , wherein the film hole protrusion bodies comprise quartz.

7. The method of claim 5 , wherein the film hole protrusion bodies are disposed on at least one of a pressure side and a suction side of the ceramic core.

8. The method of claim 1 , further comprising:
removing the ceramic core, the film hole protrusions, and the ceramic shell; and
forming a remainder of the film cooling holes in the pattern of film cooling holes.

Assignees

• Siemens Energy Inc
• Siemens Ag
• Mikro Systems Inc

Inventors

• Lee Ching-Pang
• Jiang Nan

Classifications

• B22C9/10

  Cores; Manufacture or installation of cores {(breaker cores B22C9/084)} · CPC title

• B22C9/043

  Removing the consumable pattern · CPC title

• B22C9/04

  Use of lost patterns · CPC title

• F05D2220/32

  in gas turbines · CPC title

• B22D25/02 Primary

  by its peculiarity of shape; of works of art {(cylinders, pistons B22D15/02)} · CPC title