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:

Mar. 18, 2016
Applicant:

United Technologies Corporation, Hartford, CT (US);

Inventors:

Paul W. Duesler, Manchester, CT (US);

Frederick M. Schwarz, Glastonbury, CT (US);

Assignee:

United Technologies Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 7/32 (2006.01); F28D 7/06 (2006.01); F02K 3/115 (2006.01); F02C 6/08 (2006.01); F02C 7/141 (2006.01); F02C 7/18 (2006.01); F04D 29/58 (2006.01); F28F 9/00 (2006.01); F28F 9/02 (2006.01); F28D 21/00 (2006.01);
U.S. Cl.
CPC ...
F02C 7/32 (2013.01); F02C 6/08 (2013.01); F02C 7/141 (2013.01); F02C 7/185 (2013.01); F02K 3/115 (2013.01); F04D 29/5826 (2013.01); F28D 7/06 (2013.01); F28F 9/002 (2013.01); F28F 9/0246 (2013.01); F05D 2260/213 (2013.01); F05D 2300/175 (2013.01); F28D 2021/0026 (2013.01); F28F 2255/02 (2013.01); F28F 2265/26 (2013.01); F28F 2280/00 (2013.01);
Abstract

A heat exchanger (HEX) arrangement for cooling air in a gas turbine engine is provided. The HEX arrangement may include a heat exchanger coupled to a plurality of ducts comprising a hot-side inlet duct and a hot-side outlet duct. The hot-side outlet duct may be in fluid communication with a compressor section of the gas turbine engine and in mechanical communication with a diffuser case. The HEX arrangement may further include a plurality of supporting links coupled between the heat exchanger and the gas turbine engine for securing the heat exchanger relative to the gas turbine engine. The supporting links may comprise a statically determined system. A spring rate ratio of between 1% and 30% may exist between the plurality of ducts and the plurality of supporting links.


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