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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 11970062 B1

PDFFull Text
Date of Patent:
Apr. 30, 2024

Filed:

Apr. 05, 2017

Systems and methods of power allocation for hybrid electric architecture

Applicant:

GE Aviation Systems Llc, Grand Rapids, MI (US);

Inventor:

Manish Ashvinkumar Dalal, Dayton, OH (US);

Assignee:

GE Aviation Systems LLC, Grand Rapids, MI (US);

Attorney:

Dority & Manning, P.A.

Primary Examiner:

Daniel Kessie

Int. Cl.
CPC ...
B60L 1/00 (2006.01); B60L 15/00 (2006.01); B60L 50/13 (2019.01); B60L 50/15 (2019.01); B60L 50/60 (2019.01); B60L 50/61 (2019.01); B64D 27/18 (2006.01); B64D 27/24 (2006.01); F01D 15/10 (2006.01); F02C 6/00 (2006.01); F02C 6/14 (2006.01); F02C 6/20 (2006.01); F02C 7/275 (2006.01); F02C 7/32 (2006.01); F02C 7/36 (2006.01); F02K 5/00 (2006.01); F02N 11/08 (2006.01); H02J 1/10 (2006.01); H02J 7/34 (2006.01); B64D 27/02 (2006.01); B64D 41/00 (2006.01);
U.S. Cl.
CPC ...
B60L 1/00 (2013.01); B60L 15/007 (2013.01); B60L 50/13 (2019.02); B60L 50/15 (2019.02); B60L 50/60 (2019.02); B60L 50/61 (2019.02); B64D 27/18 (2013.01); B64D 27/24 (2013.01); F01D 15/10 (2013.01); F02C 6/00 (2013.01); F02C 6/14 (2013.01); F02C 6/20 (2013.01); F02C 7/275 (2013.01); F02C 7/32 (2013.01); F02C 7/36 (2013.01); F02K 5/00 (2013.01); F02N 11/0866 (2013.01); H02J 1/102 (2013.01); H02J 7/34 (2013.01); B60L 2200/10 (2013.01); B60Y 2200/51 (2013.01); B60Y 2200/92 (2013.01); B64D 2027/026 (2013.01); B64D 41/00 (2013.01); B64D 2221/00 (2013.01); F05D 2220/50 (2013.01); F05D 2220/60 (2013.01); F05D 2220/76 (2013.01); F05D 2240/40 (2013.01); F05D 2270/20 (2013.01); Y02T 10/70 (2013.01);
Abstract

Systems and method for an electrical system on an aircraft are provided. In example embodiments, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to a load. A hybrid electric propulsion system and a secondary aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the hybrid electric propulsion system, and the secondary aircraft systems bus.

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