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:
Jul. 14, 2020

Filed:

Apr. 11, 2017
Applicant:

United Technologies Corporation, Farmington, CT (US);

Inventors:

Jonathan Ortiz, El Centro, CA (US);

Lane Mikal Thornton, Tolland, CT (US);

Matthew A. Devore, Rocky Hill, CT (US);

Assignee:

Raytheon Technologies Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 17/16 (2006.01); F01D 25/12 (2006.01); F02C 3/04 (2006.01); F01D 17/10 (2006.01); F01D 9/04 (2006.01); F01D 11/14 (2006.01); F02C 6/08 (2006.01); F01D 5/08 (2006.01); F01D 9/06 (2006.01);
U.S. Cl.
CPC ...
F01D 25/12 (2013.01); F01D 5/081 (2013.01); F01D 9/041 (2013.01); F01D 9/065 (2013.01); F01D 11/14 (2013.01); F01D 17/105 (2013.01); F01D 17/162 (2013.01); F02C 3/04 (2013.01); F02C 6/08 (2013.01); F05D 2220/32 (2013.01); F05D 2240/11 (2013.01); F05D 2240/35 (2013.01); F05D 2260/213 (2013.01); F05D 2300/50212 (2013.01); Y02T 50/676 (2013.01);
Abstract

A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor, the tapped air being passed through a heat exchanger. A vane section has vanes downstream of the combustor, but upstream of the first stage blade, and the air downstream of the heat exchanger passes radially inwardly of the combustor, along an axial length of the combustor, and then radially outwardly through a hollow chamber in the vanes, and then across the blade outer air seal, to cool the blade outer air seal.


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