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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 10677154 B1

PDFFull Text
Date of Patent:
Jun. 09, 2020

Filed:

Oct. 18, 2018

Compound engine assembly with offset turbine shaft, engine shaft and inlet duct

Applicant:

Pratt & Whitney Canada Corp., Longueuil, CA;

Inventors:

Sylvain Lamarre, Boucherville, CA;

Mike Fontaine, Boucherville, CA;

Andre Julien, Ste-Julie, CA;

Michael Gaul, Montreal, CA;

Jean Thomassin, Sainte-Julie, CA;

Lazar Mitrovic, Longueuil, CA;

Ilya Medvedev, St-Petersburg, RU;

Sergey Usikov, St-Petersburg, RU;

Andrey Zolotov, St-Petersburg, RU;

Assignee:

PRATT & WHITNEY CANADA CORP., Longueuil, QC, CA;

Attorney:

Norton Rose Fulbright Canada LLP

Primary Examiner:

Jesse S Bogue

Int. Cl.
CPC ...
F02B 41/00 (2006.01); F01C 11/00 (2006.01); F02C 6/12 (2006.01); F02C 6/20 (2006.01); F02C 7/052 (2006.01); F02C 7/36 (2006.01); F01C 21/18 (2006.01); F01C 1/22 (2006.01);
U.S. Cl.
CPC ...
F02B 41/00 (2013.01); F01C 11/008 (2013.01); F01C 21/18 (2013.01); F02C 6/12 (2013.01); F02C 6/206 (2013.01); F02C 7/052 (2013.01); F02C 7/36 (2013.01); F01C 1/22 (2013.01); F05B 2220/40 (2013.01); F05D 2220/323 (2013.01); F05D 2230/51 (2013.01); F05D 2230/72 (2013.01); F05D 2250/312 (2013.01); F05D 2260/4031 (2013.01); F05D 2300/121 (2013.01); F05D 2300/171 (2013.01);
Abstract

A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

Find Patent Forward Citations

Lamarre, Sylvain. (2020). Compound engine assembly with offset turbine shaft, engine shaft and inlet duct (U.S. Patent No. 10677154). U.S. Patent and Trademark Office. https://idiyas.com/patent/badge/10677154

Data source: USPTO (United States Patent and Trademark Office) public patent records. Weekly synchronization. How IDiyas builds this profile

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