EP 0781967 B1 20030402 - Annular combustion chamber for gas turbine
Title (en)
Annular combustion chamber for gas turbine
Title (de)
Gasturbinenringbrennkammer
Title (fr)
Chambre de combustion annulaire pour turbine à gaz
Publication
Application
Priority
DE 19549143 A 19951229
Abstract (en)
[origin: EP0781967A2] The improved burn gas turbine has the air flow taken from the last stage of the compressor (1) and ducted (15) to a premixing stage (5) where a swirl generator (16) and fuel injector (17) in each duct generates a premixing of the air and fuel. The mixture is ducted into a ring shaped combustion chamber (4). The air distribution ducts are arranged around the axis of the gas turbine in a spiral array. Downstream of the swirl generators the premixing ducts have a constant cross section. This is circular or rectangular. The relation between the number of vanes in the last stage of the compressor to the number of air ducts is a whole number, preferably 1 or 2.
IPC 1-7
IPC 8 full level
F23R 3/16 (2006.01); F23R 3/04 (2006.01); F23R 3/10 (2006.01); F23R 3/20 (2006.01); F23R 3/28 (2006.01); F23R 3/32 (2006.01); F23R 3/34 (2006.01); F23R 3/42 (2006.01); F23R 3/46 (2006.01); F23R 3/50 (2006.01)
CPC (source: EP US)
F23R 3/045 (2013.01 - EP US); F23R 3/10 (2013.01 - EP US); F23R 3/286 (2013.01 - EP US); F23R 3/50 (2013.01 - EP US); F23R 2900/03041 (2013.01 - EP US)
Designated contracting state (EPC)
DE FR GB IT
DOCDB simple family (publication)
EP 0781967 A2 19970702; EP 0781967 A3 19990407; EP 0781967 B1 20030402; CN 1088151 C 20020724; CN 1158383 A 19970903; DE 19549143 A1 19970703; DE 59610298 D1 20030508; JP H09196379 A 19970729; US 5839283 A 19981124
DOCDB simple family (application)
EP 96810777 A 19961112; CN 96123618 A 19961227; DE 19549143 A 19951229; DE 59610298 T 19961112; JP 34588096 A 19961225; US 75172196 A 19961118