EP 1265030 B1 20080709 - Mounting of a ceramic matrix composite combustion chamber with flexible shrouds
Title (en)
Mounting of a ceramic matrix composite combustion chamber with flexible shrouds
Title (de)
Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff mit flexiblen Verbindungsringen
Title (fr)
Accrochage de chambre de combustion CMC de turbomachine par viroles de liaison souples
Publication
Application
Priority
FR 0107375 A 20010606
Abstract (en)
[origin: EP1265030A1] The aircraft gas turbine engine is held in position be a flexible connecting ring which is made of metal in sectors (56,60). One end (56a,60a) of the ring is fixed (50,52) to the combustion chamber and the second end, which forms a flange, is fixed (54,58) to the envelope. The ring can be bolted to the combustion chamber. the connecting ring can be apertured for ventilation.
IPC 8 full level
F23R 3/42 (2006.01); F23R 3/50 (2006.01); F23R 3/60 (2006.01)
CPC (source: EP US)
F23R 3/60 (2013.01 - EP US); F05B 2230/606 (2013.01 - EP US)
Citation (examination)
- US 5851679 A 19981222 - STOWELL WILLIAM R [US], et al
- US 4739621 A 19880426 - PETTENGILL JASON S [US], et al
Designated contracting state (EPC)
DE FR GB
DOCDB simple family (publication)
EP 1265030 A1 20021211; EP 1265030 B1 20080709; DE 60227455 D1 20080821; FR 2825787 A1 20021213; FR 2825787 B1 20040827; JP 2002372242 A 20021226; JP 3984101 B2 20071003; US 2003000223 A1 20030102; US 6823676 B2 20041130
DOCDB simple family (application)
EP 02291359 A 20020604; DE 60227455 T 20020604; FR 0107375 A 20010606; JP 2002158746 A 20020531; US 16180502 A 20020605