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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 10961907 B1

PDFFull Text
Date of Patent:
Mar. 30, 2021

Filed:

Jun. 26, 2018

Aircraft incorporating a low-temperature bleed system

Applicant:

Airbus Operations, S.l., Madrid, ES;

Inventors:

Marta Castillo De Alvear, Getafe, ES;

Juan Tomas Prieto Padilla, Getafe, ES;

Assignee:

Airbus Operations, S.L., Getafe, ES;

Attorney:

Jenkins, Wilson, Taylor & Hunt, P.A.

Primary Examiner:

Claude J Brown

Int. Cl.
CPC ...
B64D 13/08 (2006.01); F02C 6/08 (2006.01); F02C 7/14 (2006.01); B64D 13/02 (2006.01); B64D 15/04 (2006.01); F02K 3/06 (2006.01); F02K 3/115 (2006.01); B64D 29/02 (2006.01); F02C 7/18 (2006.01); F02C 9/18 (2006.01); B64D 13/06 (2006.01); F28D 21/00 (2006.01); B64D 33/02 (2006.01);
U.S. Cl.
CPC ...
F02C 6/08 (2013.01); B64D 13/02 (2013.01); B64D 13/08 (2013.01); B64D 15/04 (2013.01); B64D 29/02 (2013.01); F02C 7/14 (2013.01); F02C 7/185 (2013.01); F02C 9/18 (2013.01); F02K 3/06 (2013.01); F02K 3/115 (2013.01); B64D 2013/0607 (2013.01); B64D 2013/0618 (2013.01); B64D 2033/024 (2013.01); B64D 2033/0233 (2013.01); F05D 2260/213 (2013.01); F28D 2021/0021 (2013.01);
Abstract

An aircraft incorporating a bleed system for extracting compressed air from the aircraft main engines to be used as a source of pressurized air for the aircraft. The bleed air system includes a first pre-cooler installed at one of the main engines nacelle and coupled with the bleed duct, and adapted for cooling down the bleed air extracted from the main engine, and a second pre-cooler installed at the pylon and coupled with bleed duct and downstream the first pre-cooler. The working temperature of the aircraft bleed system is reduced, down to max 200° C., so that the dimensions of an Over Heat Detection System (OHDS) is reduced.

Find Patent Forward Citations

Castillo De Alvear, Marta. (2021). Aircraft incorporating a low-temperature bleed system (U.S. Patent No. 10961907). U.S. Patent and Trademark Office. https://idiyas.com/patent/badge/10961907

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

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