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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.

Patent No.:

US 12583609 B1

PDFFull Text
Date of Patent:
Mar. 24, 2026

Filed:

Dec. 23, 2022

Exhaust duct for hybrid aircraft powerplant

Applicant:

Pratt & Whitney Canada Corp., Longueuil, CA;

Inventor:

David Menheere, Norval, CA;

Assignee:

Pratt & Whitney Canada Corp., Longueuil, CA;

Attorney:

Getz Balich LLC

Primary Examiner:

Jason H Duger

Int. Cl.
CPC ...
B64D 27/10 (2006.01); B64D 27/02 (2006.01); B64D 27/24 (2024.01); B64D 33/04 (2006.01); B64D 35/024 (2025.01); B64D 35/08 (2025.01); F01D 15/10 (2006.01); F01D 25/30 (2006.01); F02C 3/04 (2006.01); F02C 6/00 (2006.01); F02C 6/20 (2006.01); F02C 7/36 (2006.01); F02K 1/40 (2006.01); F02K 1/52 (2006.01); F02K 5/00 (2006.01); H02K 7/116 (2006.01); H02K 7/18 (2006.01);
U.S. Cl.
CPC ...
B64D 35/024 (2024.01); B64D 27/10 (2013.01); B64D 27/24 (2013.01); B64D 33/04 (2013.01); B64D 35/08 (2013.01); F01D 15/10 (2013.01); F02C 3/04 (2013.01); F02C 6/00 (2013.01); F02C 6/206 (2013.01); F02C 7/36 (2013.01); F02K 1/40 (2013.01); F02K 1/52 (2013.01); F02K 5/00 (2013.01); H02K 7/116 (2013.01); H02K 7/1823 (2013.01); B64D 27/026 (2024.01); B64D 33/06 (2013.01); F01D 25/30 (2013.01); F05D 2220/324 (2013.01); F05D 2220/76 (2013.01); F05D 2250/314 (2013.01);
Abstract

An aircraft system is provided that includes a propulsor rotor, an electric machine and a gas turbine engine. The electric machine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine is operatively coupled to and configured to drive rotation of the propulsor rotor. The gas turbine engine includes a compressor section, a combustor section, a turbine section, an exhaust duct and a flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust duct. The exhaust duct extends longitudinally along the electric machine. The exhaust duct extends partially circumferentially about the electric machine between opposing circumferential sides of the exhaust duct.

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