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:
Aug. 18, 2020

Filed:

Jul. 25, 2017
Applicant:

Safran Aircraft Engines, Paris, FR;

Inventors:

Nicolas Jerome Jean Tantot, Paris, FR;

Michael Sauve, Nandy, FR;

Assignee:
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 21/04 (2006.01); B64D 29/04 (2006.01); B64D 27/26 (2006.01); B64D 27/02 (2006.01); F01D 1/24 (2006.01); B64D 27/14 (2006.01); B64D 27/20 (2006.01); F02K 3/072 (2006.01); F04D 29/52 (2006.01);
U.S. Cl.
CPC ...
F01D 21/045 (2013.01); B64D 27/02 (2013.01); B64D 27/14 (2013.01); B64D 27/20 (2013.01); B64D 27/26 (2013.01); B64D 29/04 (2013.01); F01D 1/24 (2013.01); F02K 3/072 (2013.01); F04D 29/522 (2013.01); F05D 2220/323 (2013.01); F05D 2240/14 (2013.01); F05D 2240/20 (2013.01); F05D 2250/44 (2013.01); F05D 2270/09 (2013.01);
Abstract

The invention relates to an aircraft comprising a fuselage, flight control surfaces and a turbojet engine () integrated into the rear of said fuselage in the extension thereof, the turbojet engine () comprising two gas generators () that supply, via a common central duct (), a power turbine () comprising two counter-rotating rotors () respectively driving two upstream () and downstream () coaxial and counter-rotating fans each comprising a ring of vanes (), the set of fans () being integrated into a fairing () of the turbojet engine () formed at the rear of the fuselage (), characterised in that at least said fairing () is axially arranged behind the flight control surfaces and comprises an upstream section (), surrounding the upstream fan (), configured to be radially traversed by at least one fragment () of a vane () of the upstream fan () in the event of the breakage of a vane () of said upstream fan () and the ejection of said at least one fragment ().


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