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:
Apr. 02, 2019

Filed:

Oct. 27, 2015
Applicant:

United Technologies Corporation, Hartford, CT (US);

Inventors:

San Quach, East Hartford, CT (US);

Christopher King, Bristol, CT (US);

Thomas N. Slavens, Vernon, CT (US);

Assignee:

United Technologies Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/18 (2006.01); F01D 5/02 (2006.01); F01D 9/04 (2006.01); F02C 3/04 (2006.01); F02C 7/18 (2006.01); F23R 3/00 (2006.01); F01D 11/08 (2006.01); F01D 25/12 (2006.01);
U.S. Cl.
CPC ...
F01D 5/187 (2013.01); F01D 5/02 (2013.01); F01D 5/186 (2013.01); F01D 9/041 (2013.01); F01D 11/08 (2013.01); F01D 25/12 (2013.01); F02C 3/04 (2013.01); F02C 7/18 (2013.01); F23R 3/002 (2013.01); F05D 2220/32 (2013.01); F05D 2230/10 (2013.01); F05D 2240/12 (2013.01); F05D 2240/30 (2013.01); F05D 2240/307 (2013.01); F05D 2240/35 (2013.01); F05D 2250/231 (2013.01); F05D 2250/232 (2013.01); F05D 2260/202 (2013.01); Y02T 50/676 (2013.01);
Abstract

A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.


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