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. 15, 2024

Filed:

Jan. 19, 2022
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Brandon Wayne Miller, Liberty Township, OH (US);

Scott David Hunter, Seattle, WA (US);

Patrick Michael Marrinan, Cincinnati, OH (US);

Scott Alan Schimmels, Miamisburg, OH (US);

Assignee:

General Electric Company, Evendale, OH (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 6/08 (2006.01); B64D 13/06 (2006.01); F02C 9/00 (2006.01); F02C 9/18 (2006.01); F02K 3/04 (2006.01);
U.S. Cl.
CPC ...
F02C 6/08 (2013.01); B64D 13/06 (2013.01); F02C 9/00 (2013.01); F02C 9/18 (2013.01); F02K 3/04 (2013.01); B64D 2013/0603 (2013.01); B64D 2013/0607 (2013.01); B64D 2013/0618 (2013.01); B64D 2013/0648 (2013.01); F05D 2220/32 (2013.01); F05D 2220/76 (2013.01);
Abstract

A gas turbine engine includes a turbomachine, the turbomachine defining a core flow therethrough during operation. A first heat exchange assembly is in fluid communication with the turbomachine for receiving a first bleed flow from the turbomachine. A second heat exchange assembly is in fluid communication with the turbomachine for receiving a second bleed flow from the turbomachine. A first flow outlet is provided for receiving the first bleed flow from the first heat exchange assembly and providing the first bleed flow to a first aircraft flow assembly. A second flow outlet is provided for receiving the second bleed flow and providing the second bleed flow from the second heat exchange assembly to a second aircraft flow assembly.


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