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:
Sep. 25, 2018

Filed:

Jul. 21, 2016
Applicant:

Safran Aircraft Engines, Paris, FR;

Inventors:

Francois Gallet, Moissy-Cramayel, FR;

Nicolas Jerome Jean Tantot, Moissy-Cramayel, FR;

Assignee:
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 17/14 (2006.01); B64D 27/20 (2006.01); F02K 3/072 (2006.01); F02K 3/12 (2006.01); F01D 17/16 (2006.01); B64D 27/14 (2006.01); F01D 1/02 (2006.01); B64C 11/48 (2006.01); F01D 1/24 (2006.01); F02K 3/075 (2006.01); F02K 3/077 (2006.01); F01D 17/10 (2006.01);
U.S. Cl.
CPC ...
F01D 17/141 (2013.01); B64C 11/48 (2013.01); B64D 27/14 (2013.01); B64D 27/20 (2013.01); F01D 1/023 (2013.01); F01D 1/24 (2013.01); F01D 17/105 (2013.01); F01D 17/14 (2013.01); F01D 17/145 (2013.01); F01D 17/148 (2013.01); F01D 17/16 (2013.01); F01D 17/162 (2013.01); F01D 17/167 (2013.01); F02K 3/072 (2013.01); F02K 3/075 (2013.01); F02K 3/077 (2013.01); F02K 3/12 (2013.01); F05D 2220/323 (2013.01); F05D 2240/128 (2013.01); F05D 2260/606 (2013.01); F05D 2270/093 (2013.01); F05D 2270/102 (2013.01);
Abstract

The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (), the turbine engine being incorporated at the rear of a fuselage () of the aircraft, in the extension of same and comprising at least two gas generators () that supply, via a shared central stream (), a power turbine (), the turbine () comprising two contrarotating rotors () for driving two fans () disposed downstream from the gas generators (), said aircraft comprising means () arranged for separating the gas flow in the power turbine () into at least two concentric streams () and a device comprising first means for distributing the gas flow (-) between said streams () from the central stream (), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream () of the streams () of the power turbine ().


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