The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Sep. 10, 2019

Filed:

May. 01, 2015
Applicant:

United Technologies Corporation, Hartford, CT (US);

Inventors:

Matthew S. Gleiner, Norwalk, CT (US);

Bret M. Teller, Meriden, CT (US);

James T. Auxier, Bloomfield, CT (US);

Assignee:

UNITED TECHNOLOGIES CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 5/14 (2006.01); F01D 5/18 (2006.01); B22C 9/10 (2006.01); B22D 15/00 (2006.01); B22D 17/00 (2006.01); B22C 9/06 (2006.01); B22D 25/02 (2006.01); F01D 5/02 (2006.01); F01D 9/04 (2006.01); F01D 11/08 (2006.01); F01D 25/12 (2006.01);
U.S. Cl.
CPC ...
B22C 9/101 (2013.01); B22C 9/06 (2013.01); B22C 9/103 (2013.01); B22D 15/00 (2013.01); B22D 17/00 (2013.01); B22D 25/02 (2013.01); F01D 5/02 (2013.01); F01D 5/14 (2013.01); F01D 5/147 (2013.01); F01D 5/187 (2013.01); F01D 9/041 (2013.01); F01D 11/08 (2013.01); F01D 25/12 (2013.01); F05D 2220/32 (2013.01); F05D 2230/21 (2013.01); F05D 2230/211 (2013.01); F05D 2260/202 (2013.01);
Abstract

A casting core for an airfoil according to an example of the present disclosure includes, among other things, a first portion extending in a first direction and corresponding to a first cavity of an airfoil. The first portion defines a reference plane along a parting line formed by a casting die. The first portion defines a plurality of grooves corresponding to a plurality of trip strips of the airfoil. Each of the plurality of grooves defines a respective groove axis, and the plurality of grooves are distributed in the first direction along a first side of the reference plane such that one or more of the groove axes are oriented with respect to a pull direction of the casting die. A method for fabricating a gas turbine engine component is also disclosed.


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