Method and casting core for forming a landing for welding a baffle inserted in an airfoil

Patent metadata

Field	Value
Publication number	US-9403208-B2
Application number	US-98163010-A
Country	US
Kind code	B2
Filing date	Dec 30, 2010
Priority date	Dec 30, 2010
Publication date	Aug 2, 2016
Grant date	Aug 2, 2016

Abstract

A method and casting core for forming a landing for welding a baffle inserted into an airfoil are disclosed, wherein the baffle landing of the blade or vane is formed in investment casting by the casting core rather than by wax, reducing tolerances and variability in the location of the baffle inserted into the cooling cavity of airfoil when the baffle is welded to the baffle landing.

First claim

I claim:

1. A casting core for forming a first landing of a cooling cavity of an airfoil, the airfoil having an outer platform and an inner platform,
the casting core extending longitudinally between an outer platform end of the casting core and an inner platform end of the casting core,
the casting core comprising:
a first portion in the shape of the first landing, the first portion being configured to mold the first landing as a surface of the airfoil on which a first baffle is welded, and the first portion being disposed solely at the outer platform end of the casting core;
a second portion in the shape of a second landing for welding a second baffle inserted into the cooling cavity, the second portion being configured to mold the second landing as a surface of the airfoil on which the second baffle is welded, and the second portion being disposed solely at the inner platform end of the casting core;
a third portion in the shape of the cooling cavity, the third portion extending longitudinally between the first portion and the second portion;
the first portion and the second portion substantially perpendicularly extending beyond the entirety of the third portion perimeter; and
the first portion and the second portion directly opposing each other on opposing ends of the longitudinally extending third portion.

2. The casting core of claim 1 , wherein the first portion and the second portion each have an outer diameter that exceeds a maximum outer diameter of the third portion.

3. The casting core of 2 , wherein the second portion is further configured to mold the second landing as a surface located on the inner platform of the airfoil.

4. The casting core of claim 1 , wherein the casting core is a ceramic polymer.

5. The casting core of claim 1 , wherein the casting core is a refractory metal core.

6. The casting core of claim 1 , wherein the first portion is further configured to mold the first landing as a surface located on the outer platform of the airfoil.

Assignees

• Propheter-Hinckley Tracy A
• United Technologies Corp

Inventors

• Propheter-Hinckley Tracy A

Classifications

• B22C9/04 Primary

  Use of lost patterns · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• B22C1/00

  Compositions of refractory mould or core materials; Grain structures thereof (refractory materials in general C04B35/00); Chemical or physical features in the formation or manufacture of moulds · CPC title

• B22C9/103

  Multipart cores · CPC title

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title