EP 0602404 B1 19970903 - Gas turbine combustor
Title (en)
Gas turbine combustor
Title (de)
Gasturbinenbrennkammer
Title (fr)
Chambre de combustion pour turbine à gaz
Publication
Application
Priority
DE 4242650 A 19921217
Abstract (en)
[origin: EP0602404A1] A gas-turbine combustion chamber consists of an inflow region (1) with (fuel) injection, an ignition delay region (2), reaction region (3), combustion region (4) and transition region (5) to the turbine. In the combustion chamber, the reaction region (3) has a cross-section which widens in such a way that combustion can be carried out in terms of gas dynamics at constant pressure or constant Mach number. As a result, the total pressure loss and the combustion chamber length required for combustion are reduced, and this is seen in an improvement in the efficiency and performance (output). <IMAGE>
IPC 1-7
IPC 8 full level
F23R 3/16 (2006.01); F23R 3/02 (2006.01); F23R 3/42 (2006.01)
CPC (source: EP US)
Designated contracting state (EPC)
DE FR GB
DOCDB simple family (publication)
EP 0602404 A1 19940622; EP 0602404 B1 19970903; DE 4242650 A1 19940623; DE 59307265 D1 19971009; JP H06221557 A 19940809; US 5465577 A 19951114
DOCDB simple family (application)
EP 93118569 A 19931118; DE 4242650 A 19921217; DE 59307265 T 19931118; JP 31668993 A 19931216; US 33929294 A 19941110