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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 9991763 B1

PDFFull Text
Date of Patent:
Jun. 05, 2018

Filed:

Jun. 07, 2017

Gas turbine engine with multiple electric generators

Applicant:

Florida Turbine Technologies, Inc., Jupiter, FL (US);

Inventors:

James P Downs, Hobe Sound, FL (US);

Robert L Memmen, Stuart, FL (US);

Assignee:

Florida Turbine Technologies, Inc., Jupiter, FL (US);

Attorney:

John Ryznic

Primary Examiner:

Pedro J Cuevas

Int. Cl.
CPC ...
F02B 63/04 (2006.01); H02K 7/10 (2006.01); H02K 7/18 (2006.01); F01D 15/10 (2006.01); F01D 15/12 (2006.01); B64D 27/10 (2006.01); B64D 27/24 (2006.01); B64D 35/02 (2006.01); B64C 39/02 (2006.01); H02K 7/116 (2006.01); H02K 7/108 (2006.01); F02D 29/06 (2006.01); H02P 9/04 (2006.01); B64D 27/02 (2006.01);
U.S. Cl.
CPC ...
H02K 7/1823 (2013.01); B64C 39/024 (2013.01); B64D 27/10 (2013.01); B64D 27/24 (2013.01); B64D 35/02 (2013.01); F01D 15/10 (2013.01); F01D 15/12 (2013.01); H02K 7/108 (2013.01); H02K 7/116 (2013.01); B64C 2201/042 (2013.01); B64C 2201/048 (2013.01); B64D 2027/026 (2013.01); F05D 2220/323 (2013.01); F05D 2240/60 (2013.01); F05D 2260/40311 (2013.01);
Abstract

A power plant for a small aircraft with a gas turbine engine that drives a number of electric generators, where a gear box transmit power from the engine shaft to the number of generators, the gear box having a single input shaft that drives a number of driven gears with each driven gear having a generator drive shaft that extends out both sides, and an electric generator connected to each side of the drive shaft. A compact arrangement of generators are formed where each generator can be disengaged from the drive shaft to regulate total electrical output or to prevent a damaged generator from causing damage to other parts of the system or aircraft.

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