EP 2107314 A1 20091007 - Combustor for a gas turbine
Title (en)
Combustor for a gas turbine
Title (de)
Verbrennungskammer für eine Gasturbine
Title (fr)
Chambre de combustion pour turbine à gaz
Publication
Application
Priority
EP 08006656 A 20080401
Abstract (en)
The present invention provides a combustor (12) for a gas turbine (10). The combustor (12) comprises an annular passage (25) defined by a combustor liner (20) and an outer shell (22). The annular passage (25) forms a first portion of a flow-path (26) for air, to provide cooling of said combustor liner (20). The annular passage (25) is upstream of a burner (36) and in serial flow communication with said burner (36). The proposed combustor (12) further includes a perforated structure (32) connecting the combustor liner (20) and the outer shell (22). The structure (32) is perforated with a multiplicity of openings (33) adapted to provide an outlet of air from said annular passage (25) to said burner (36) with a predetermined pressure drop.
IPC 8 full level
CPC (source: EP)
F23R 3/005 (2013.01); F23R 3/50 (2013.01); F23R 3/54 (2013.01); F23R 2900/03042 (2013.01)
Citation (search report)
[X] US 6220034 B1 20010424 - MOWILL R JAN [NL]
Designated contracting state (EPC)
AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR
Designated extension state (EPC)
AL BA MK RS
DOCDB simple family (publication)
DOCDB simple family (application)
EP 08006656 A 20080401; EP 2009053701 W 20090330