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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 11757386 B1

PDFFull Text
Date of Patent:
Sep. 12, 2023

Filed:

Feb. 17, 2022

Hybrid electric propulsion system and method of operation

Applicant:

Pratt & Whitney Canada Corp., Longueuil, CA;

Inventors:

Eric Latulipe, Ste-Julie, CA;

Richard Freer, Saint-Basile-le-Grand, CA;

Assignee:

PRATT & WHITNEY CANADA CORP., Longueuil, CA;

Attorney:

Norton Rose Fulbright Canada LLP

Primary Examiner:

Viet P Nguyen

Int. Cl.
CPC ...
H02P 6/12 (2006.01); B60L 50/13 (2019.01); B60L 50/60 (2019.01); B60L 53/24 (2019.01); B60L 50/51 (2019.01); B64D 27/02 (2006.01); B64D 27/10 (2006.01); B64D 27/12 (2006.01); B64D 27/24 (2006.01); B64D 27/26 (2006.01); B64D 31/00 (2006.01); B64D 31/06 (2006.01); B64D 35/00 (2006.01); B64D 35/02 (2006.01); B64D 35/08 (2006.01); F01D 15/10 (2006.01); F02K 3/06 (2006.01); G08C 19/38 (2006.01); H02K 19/34 (2006.01); H02K 41/03 (2006.01); H02K 47/04 (2006.01); H02K 51/00 (2006.01); H02P 5/74 (2006.01); H02P 6/00 (2016.01); H02P 9/00 (2006.01); H02P 17/00 (2006.01); H02P 29/024 (2016.01); H02P 29/028 (2016.01); H02P 101/25 (2016.01); H02P 101/30 (2015.01); H02P 27/06 (2006.01);
U.S. Cl.
CPC ...
H02P 6/12 (2013.01); B60L 50/13 (2019.02); B60L 50/51 (2019.02); B60L 50/60 (2019.02); B60L 53/24 (2019.02); B64D 27/02 (2013.01); B64D 27/10 (2013.01); B64D 27/12 (2013.01); B64D 27/24 (2013.01); B64D 27/26 (2013.01); B64D 31/00 (2013.01); B64D 31/06 (2013.01); B64D 35/00 (2013.01); B64D 35/02 (2013.01); B64D 35/08 (2013.01); F01D 15/10 (2013.01); F02K 3/06 (2013.01); G08C 19/38 (2013.01); H02K 19/34 (2013.01); H02K 41/03 (2013.01); H02K 47/04 (2013.01); H02K 51/00 (2013.01); H02P 5/74 (2013.01); H02P 6/005 (2013.01); H02P 9/008 (2013.01); H02P 17/00 (2013.01); H02P 29/025 (2013.01); H02P 29/028 (2013.01); B60L 2200/10 (2013.01); B60L 2210/42 (2013.01); B60L 2220/20 (2013.01); B64D 2027/026 (2013.01); F05D 2220/323 (2013.01); F05D 2220/764 (2013.01); H02K 2213/06 (2013.01); H02P 27/06 (2013.01); H02P 2101/25 (2015.01); H02P 2101/30 (2015.01);
Abstract

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

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