EP 1265031 A1 20021211 - Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials
Title (en)
Fixing of metallic cowls on turbomachine combustion chamber liners made of CMC materials
Title (de)
Befestigung von metallischen Aufsätzen auf CMC-Turbomaschinenbrennkammerwänden
Title (fr)
Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine
Publication
Application
Priority
FR 0107374 A 20010606
Abstract (en)
The combustion chamber for an aircraft gas turbine engine has inner (28) and outer (26) composite walls and a metal base (30) held in position by the walls. The base fixings extend across annular cavities (42,44) which receive the cylindrical sections of the ends of the walls. This defines a play between the peripheral edges of the base and the returned sections (46,48) and the opposing surfaces of the walls. This allows a radial expansion of the chamber base with respect to the walls.
IPC 1-7
IPC 8 full level
F02C 7/00 (2006.01); F02C 7/20 (2006.01); F23R 3/00 (2006.01); F23R 3/42 (2006.01); F23R 3/60 (2006.01)
CPC (source: EP US)
F23R 3/007 (2013.01 - EP US); F23R 3/60 (2013.01 - EP US); F23D 2211/00 (2013.01 - EP US)
Citation (search report)
- [PXA] EP 1152191 A2 20011107 - GEN ELECTRIC [US]
- [A] US 5291732 A 19940308 - HALILA ELY E [US]
- [A] US 3911672 A 19751014 - IRWIN JOHN A
Designated contracting state (EPC)
DE FR GB
DOCDB simple family (publication)
EP 1265031 A1 20021211; EP 1265031 B1 20070912; DE 60222324 D1 20071025; DE 60222324 T2 20080612; FR 2825786 A1 20021213; FR 2825786 B1 20031017; JP 2003021335 A 20030124; JP 3984104 B2 20071003; US 2002184886 A1 20021212; US 6655148 B2 20031202
DOCDB simple family (application)
EP 02291360 A 20020604; DE 60222324 T 20020604; FR 0107374 A 20010606; JP 2002161065 A 20020603; US 16072902 A 20020605