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:
Oct. 19, 2021

Filed:

Oct. 24, 2014
Applicant:

United Technologies Corporation, Hartford, CT (US);

Inventors:

James M. Koonankeil, Marlborough, CT (US);

Edward F Pietraszkiewicz, Southington, CT (US);

Francis M Tamiso, Manchester, CT (US);

Kirk D Hlavaty, East Hartford, CT (US);

Assignee:

RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 5/14 (2006.01); F01D 11/00 (2006.01); F01D 5/18 (2006.01); F01D 11/08 (2006.01); F01D 9/06 (2006.01);
U.S. Cl.
CPC ...
F01D 5/141 (2013.01); F01D 5/186 (2013.01); F01D 5/187 (2013.01); F01D 5/188 (2013.01); F01D 9/065 (2013.01); F01D 11/00 (2013.01); F01D 11/003 (2013.01); F01D 11/08 (2013.01); F05D 2240/126 (2013.01); F05D 2240/127 (2013.01); F05D 2260/2212 (2013.01); F05D 2260/22141 (2013.01); Y02T 50/60 (2013.01); Y10T 29/49341 (2015.01);
Abstract

A cooling circuit for a gas turbine engine includes a gas turbine engine component having at least one internal cooling cavity defined by an internal wall surface and a plurality of turbulent flow features extending outwardly from the internal wall surface. Each turbulent flow feature is spaced apart from an adjacent turbulent flow feature in a first direction. At least one trench extends through the turbulent flow features in the first direction, and a plurality of cooling holes are formed within the at least one trench. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine component are also disclosed.


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