EP 2742230 A1 20140618 - EXHAUST CONE FOR AIRCRAFT TURBOJET ENGINE
Title (en)
EXHAUST CONE FOR AIRCRAFT TURBOJET ENGINE
Title (de)
AUSLASSKONUS FÜR EINEN FLUGZEUGTURBODÜSENMOTOR
Title (fr)
CÔNE D'ÉJECTION POUR TURBORÉACTEUR D'AÉRONEF
Publication
Application
Priority
- FR 1157321 A 20110812
- FR 2012051583 W 20120705
Abstract (en)
[origin: WO2013024218A1] The present invention relates to an exhaust cone for an aircraft turbojet engine comprising a front part having a front end fitted with a connecting flange (9a) for connection to a turbojet engine outlet and/or a rear end fitted with a connecting flange (9b) for connection to a rear part of the exhaust cone, said front part also being equipped with at least one noise attenuation structure comprising a corresponding external skin (52), characterized in that the external skin straddles at least part of the corresponding upstream or downstream connecting flange and is assembled therewith.
IPC 8 full level
F02K 1/04 (2006.01); F02K 1/44 (2006.01); F02K 1/80 (2006.01); F02K 1/82 (2006.01)
CPC (source: EP US)
F02K 1/04 (2013.01 - EP US); F02K 1/44 (2013.01 - EP US); F02K 1/80 (2013.01 - EP US); F02K 1/827 (2013.01 - EP US); F05D 2230/232 (2013.01 - EP US); F05D 2250/283 (2013.01 - EP US); F05D 2260/30 (2013.01 - EP US); Y02T 50/60 (2013.01 - EP US)
Citation (search report)
See references of WO 2013024218A1
Designated contracting state (EPC)
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
DOCDB simple family (publication)
FR 2978989 A1 20130215; FR 2978989 B1 20130726; BR 112014001679 A2 20170307; CA 2842874 A1 20130221; CN 103717870 A 20140409; EP 2742230 A1 20140618; RU 2014108721 A 20150920; US 2014158458 A1 20140612; US 9051899 B2 20150609; WO 2013024218 A1 20130221
DOCDB simple family (application)
FR 1157321 A 20110812; BR 112014001679 A 20120705; CA 2842874 A 20120705; CN 201280039233 A 20120705; EP 12744051 A 20120705; FR 2012051583 W 20120705; RU 2014108721 A 20120705; US 201414177494 A 20140211