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:
Dec. 11, 2018

Filed:

Feb. 11, 2016
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Thomas Lipinski, Monroe, OH (US);

Donald George LaChapelle, Cincinnati, OH (US);

Kenneth Jay Moore, Hamilton, OH (US);

Bradford Tracey, Cold Spring, KY (US);

Stephen Joseph Waymeyer, Batavia, OH (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorneys:
Primary Examiner:
Int. Cl.
CPC ...
F01D 25/14 (2006.01); F01D 11/00 (2006.01); F01D 17/08 (2006.01); F01D 17/10 (2006.01); F01D 17/14 (2006.01); F01D 25/12 (2006.01); F01D 25/24 (2006.01); F01D 9/06 (2006.01); F01D 25/16 (2006.01); F02C 7/12 (2006.01);
U.S. Cl.
CPC ...
F01D 25/14 (2013.01); F01D 9/065 (2013.01); F01D 11/005 (2013.01); F01D 17/085 (2013.01); F01D 17/105 (2013.01); F01D 17/145 (2013.01); F01D 25/12 (2013.01); F01D 25/145 (2013.01); F01D 25/162 (2013.01); F01D 25/24 (2013.01); F02C 7/12 (2013.01); F05D 2220/32 (2013.01); F05D 2260/20 (2013.01); Y02T 50/675 (2013.01);
Abstract

A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring.


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