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:
Apr. 26, 2022

Filed:

Feb. 19, 2020
Applicant:

Pratt & Whitney Canada Corp., Longueuil, CA;

Inventors:

Richard Ullyott, St-Bruno, CA;

Anthony Jones, San Diego, CA (US);

Andre Julien, Ste-Julie, CA;

Jean Thomassin, Ste-Julie, CA;

Assignee:
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02B 63/04 (2006.01); B64D 41/00 (2006.01); F01C 1/22 (2006.01); F01C 11/00 (2006.01); F02B 37/013 (2006.01); F02B 53/02 (2006.01); F02C 7/36 (2006.01); B64D 13/06 (2006.01); F02B 53/00 (2006.01);
U.S. Cl.
CPC ...
F02B 63/04 (2013.01); B64D 41/00 (2013.01); F01C 1/22 (2013.01); F01C 11/008 (2013.01); F02B 37/013 (2013.01); F02B 53/02 (2013.01); F02C 7/36 (2013.01); B64D 2013/0611 (2013.01); F02B 2053/005 (2013.01); F05B 2220/50 (2013.01); F05B 2260/211 (2013.01); F05B 2260/40 (2013.01); Y02T 10/12 (2013.01); Y02T 50/40 (2013.01); Y02T 50/50 (2013.01); Y02T 50/60 (2013.01);
Abstract

A compound engine assembly for use as an auxiliary power unit for an aircraft and including an engine core with internal combustion engine(s), a compressor having an outlet in fluid communication with an engine core inlet, a bleed conduit in fluid communication with the compressor outlet through a bleed air valve, and a turbine section having an inlet in fluid communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in fluid communication with the engine core outlet and a second stage turbine having an inlet in fluid communication the first stage turbine outlet. A method of providing compressed air and electrical power to an aircraft is also discussed.


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