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:
Mar. 10, 2020

Filed:

Dec. 30, 2014
Applicants:

Rolls-royce Corporation, Indianapolis, IN (US);

Rolls-royce North American Technologies, Inc., Indianapolis, IN (US);

Inventors:

Curtis H. Cline, Brownsburg, IN (US);

Michael J. Armstrong, Avon, IN (US);

Assignees:

Rolls-Royce North American Technologies, Inc., Indianapolis, IN (US);

Rolls-Royce Corporation, Indianapolis, IN (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 6/14 (2006.01); B64D 31/12 (2006.01); F02C 7/32 (2006.01); F02C 9/48 (2006.01); F01D 15/10 (2006.01); F02C 7/36 (2006.01); F02C 9/00 (2006.01);
U.S. Cl.
CPC ...
B64D 31/12 (2013.01); F01D 15/10 (2013.01); F02C 6/14 (2013.01); F02C 7/32 (2013.01); F02C 7/36 (2013.01); F02C 9/00 (2013.01); F02C 9/48 (2013.01); F05D 2220/60 (2013.01); F05D 2220/76 (2013.01); F05D 2260/42 (2013.01); F05D 2270/05 (2013.01); F05D 2270/335 (2013.01);
Abstract

An integrated gas turbine engine, electrical power subsystem and thermal management subsystem for aerospace application includes a first motor/generator coupled to a low pressure (LP) shaft of the gas turbine engine, a second motor/generator coupled to a high pressure (HP) shaft of the gas turbine engine, and a system controller coupled to each of the gas turbine engine, a first motor generator and a second motor/generator, wherein the controller receives engine thrust demand and electrical power demand and is programmed to determine total system power demand and the amount of power sharing between the first motor/generator and the second motor/generator to meet thrust and electrical power demand.


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