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:
Oct. 01, 2019

Filed:

Sep. 24, 2015
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, Ste-Julie, CA;

Ilya B. Medvedev, St-Petersburg, RU;

Sergey Usikov, St-Petersburg, RU;

Andrey Zolotov, St-Petersburg, RU;

Assignee:

Pratt & Whitney Canada Corp., Longueuil, Quebec, CA;

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F02C 7/047 (2006.01); F02C 6/12 (2006.01); F02C 7/14 (2006.01); F01C 11/00 (2006.01); F01C 21/06 (2006.01); F01C 21/18 (2006.01); F02B 41/00 (2006.01); F02C 3/04 (2006.01); F02C 6/18 (2006.01); F02C 7/36 (2006.01); F02B 39/04 (2006.01); F02C 7/052 (2006.01); F02B 37/00 (2006.01); F02B 33/40 (2006.01); F01C 1/22 (2006.01);
U.S. Cl.
CPC ...
F02C 7/047 (2013.01); F01C 11/008 (2013.01); F01C 21/06 (2013.01); F01C 21/18 (2013.01); F02B 33/40 (2013.01); F02B 37/00 (2013.01); F02B 39/04 (2013.01); F02B 41/00 (2013.01); F02C 3/04 (2013.01); F02C 6/12 (2013.01); F02C 6/18 (2013.01); F02C 7/052 (2013.01); F02C 7/14 (2013.01); F02C 7/36 (2013.01); F01C 1/22 (2013.01); F05B 2220/40 (2013.01); F05D 2220/40 (2013.01); F05D 2250/312 (2013.01); Y02T 10/17 (2013.01);
Abstract

A compound engine assembly with an inlet duct having an inlet surrounded by an inlet lip including at least one conduit extending therethrough, a compressor, an engine core including at least one internal combustion engine, a turbine section having a turbine shaft in driving engagement with the engine shaft, and an exhaust conduit providing a fluid communication between the outlet of the turbine section and the conduit(s) of the inlet lip. An exhaust duct and ant exhaust conduit providing a fluid communication between the outlet of the turbine section and the exhaust duct may also be provided. The internal combustion engine(s) may be rotary engine(s). A method of driving a rotatable load of an aircraft is also discussed.


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