EP 0813670 B1 20000628 - AXIALLY STEPPED DOUBLE-RING COMBUSTION CHAMBER FOR A GAS TURBINE
Title (en)
AXIALLY STEPPED DOUBLE-RING COMBUSTION CHAMBER FOR A GAS TURBINE
Title (de)
AXIAL GESTUFTE DOPPELRING-BRENNKAMMER EINER GASTURBINE
Title (fr)
CHAMBRE DE COMBUSTION A ANNEAU DOUBLE ET ETAGEMENT AXIAL POUR UNE TURBINE A GAZ
Publication
Application
Priority
- DE 19508109 A 19950308
- DE 19600837 A 19960112
- EP 9600895 W 19960304
Abstract (en)
[origin: WO9627766A1] The invention concerns an axially stepped annular combustion chamber, in particular for an aircraft gas turbine, the combustion chamber essentially comprising an independent main combustion chamber (5') and an independent pilot combustion chamber (5). Appropriate design of the inner boundary walls (6a, 6b) of the pilot combustion chamber (5) ensures that the combustion gases thereof enter the main combustion zone (5') substantially in the radial direction. As a result, optimum mixing of the fuel and air is thus ensured in this main combustion zone or main combustion chamber (5'), exhaust gas emissions are minimized and the temperature distribution at the combustion chamber outlet (8) is optimum. The inner boundary wall (6a) can comprise a deflection section (12) or the outer wall section (6b) can be inclined towards the pilot burner longitudinal axis (3a), such that the cross-section of the pilot burner zone (5) decreases in the direction of flow.
IPC 1-7
IPC 8 full level
F23R 3/34 (2006.01)
CPC (source: EP US)
F23R 3/34 (2013.01 - EP US)
Designated contracting state (EPC)
DE FR GB
DOCDB simple family (publication)
WO 9627766 A1 19960912; CA 2216115 A1 19960912; DE 59605505 D1 20000803; EP 0813670 A1 19971229; EP 0813670 B1 20000628; US 6058710 A 20000509
DOCDB simple family (application)
EP 9600895 W 19960304; CA 2216115 A 19960304; DE 59605505 T 19960304; EP 96904099 A 19960304; US 91312397 A 19970908