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:
Feb. 21, 2023

Filed:

Jun. 03, 2020
Applicant:

Pratt & Whiiney 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 ...
B64D 41/00 (2006.01); F02C 7/32 (2006.01); B64D 13/06 (2006.01); F02C 6/08 (2006.01); F01C 1/22 (2006.01); F02B 63/04 (2006.01); F02B 41/10 (2006.01); F02C 7/06 (2006.01); F02C 7/36 (2006.01); F01D 25/18 (2006.01); F02B 33/40 (2006.01); F02B 55/00 (2006.01); F01D 17/20 (2006.01); B64D 33/08 (2006.01); F01C 11/00 (2006.01); F02C 9/18 (2006.01); F02C 7/16 (2006.01); F01C 21/00 (2006.01); F01C 21/06 (2006.01);
U.S. Cl.
CPC ...
B64D 41/00 (2013.01); B64D 13/06 (2013.01); B64D 33/08 (2013.01); F01C 1/22 (2013.01); F01C 11/008 (2013.01); F01C 21/008 (2013.01); F01C 21/06 (2013.01); F01D 17/20 (2013.01); F01D 25/18 (2013.01); F02B 33/40 (2013.01); F02B 41/10 (2013.01); F02B 55/00 (2013.01); F02B 63/042 (2013.01); F02C 6/08 (2013.01); F02C 7/06 (2013.01); F02C 7/16 (2013.01); F02C 7/32 (2013.01); F02C 7/36 (2013.01); F02C 9/18 (2013.01); B64D 2013/0611 (2013.01); B64D 2013/0618 (2013.01); B64D 2041/002 (2013.01); F05D 2220/50 (2013.01); F05D 2220/76 (2013.01); F05D 2260/211 (2013.01); Y02T 10/12 (2013.01); Y02T 50/40 (2013.01); Y02T 50/50 (2013.01);
Abstract

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.


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