EP 3201531 B1 20190227 - TURBOMACHINE COMBUSTION CHAMBER
Title (en)
TURBOMACHINE COMBUSTION CHAMBER
Title (de)
BRENNKAMMER EINER TURBOMASCHINE
Title (fr)
CHAMBRE DE COMBUSTION DE TURBOMACHINE
Publication
Application
Priority
- FR 1459362 A 20141001
- FR 2015052588 W 20150929
Abstract (en)
[origin: WO2016051067A1] The invention relates to a combustion chamber for a turbomachine, such as an aircraft turbojet engine or turboprop engine, comprising an internal annular shroud and an external annular shroud which at their upstream ends are connected by an annular chamber end wall (48), said chamber comprising deflectors (50) mounted upstream of the annular chamber end wall (48). Injectors (19) are mounted in sleeves (44) at least one of which comprises a radially annular flange (66) which is designed to slide radially between the chamber end wall (48) and the deflector (50) and which is blocked axially between the chamber end wall (48) and the deflector (50).
IPC 8 full level
F23R 3/28 (2006.01); F23R 3/50 (2006.01); F23R 3/60 (2006.01)
CPC (source: EP US)
F23R 3/283 (2013.01 - EP US); F23R 3/50 (2013.01 - EP US); F23R 3/60 (2013.01 - EP US); F23R 3/10 (2013.01 - US); F23R 3/16 (2013.01 - US); F23R 3/28 (2013.01 - US); F23R 2900/00017 (2013.01 - US); F23R 2900/03041 (2013.01 - US); F23R 2900/03042 (2013.01 - US)
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)
WO 2016051067 A1 20160407; EP 3201531 A1 20170809; EP 3201531 B1 20190227; FR 3026827 A1 20160408; FR 3026827 B1 20190607; US 10488049 B2 20191126; US 2017299192 A1 20171019
DOCDB simple family (application)
FR 2015052588 W 20150929; EP 15785163 A 20150929; FR 1459362 A 20141001; US 201515516070 A 20150929