EP 2442030 A1 20120418 - Axial stage for a burner with a stabilised jet
Title (en)
Axial stage for a burner with a stabilised jet
Title (de)
Axiale Stufe für einen strahlstabilisierten Brenner
Title (fr)
Étage axial pour un brûleur à rayonnement stabilisé
Publication
Application
Priority
EP 10187400 A 20101013
Abstract (en)
The combustion system (1) comprises a first axial stage (20), a combustion chamber with a combustion chamber cross-sectional area, jet nozzles arranged in the combustion chamber with a total jet nozzle outlet cross sectional area, and a second axial stage (21) having air nozzles (22) of the first axial stage, where fuel nozzles (23) are arranged in the second axial stage. The second axial stage is downstream of the flow direction of a combustion gas, and includes burner air (20-30%). The air nozzles and the fuel nozzles are inclined in the flow direction of a combustion gas. The combustion system (1) comprises a first axial stage (20), a combustion chamber with a combustion chamber cross-sectional area, jet nozzles arranged in the combustion chamber with a total jet nozzle outlet cross sectional area, and a second axial stage (21) having air nozzles (22) of the first axial stage, where fuel nozzles (23) are arranged in the second axial stage. The second axial stage is downstream of the flow direction of a combustion gas, and includes burner air (20-30%). The air nozzles and the fuel nozzles are inclined in the flow direction of a combustion gas, where fuel lances are arranged at the upstream end of the jet nozzles. The jet nozzles are: designed such that a ratio of the combustion chamber cross-sectional area to the total jet nozzle outlet cross sectional area is 10; and annularly arranged around a central axis of the combustor. A ratio of the distance between the jet nozzle outlet of the first axial stage and the air nozzles of the second axial stage and the diameter of the jet nozzles is 8-15.
Abstract (de)
Die Erfindung betrifft ein Verbrennungssystem (1) mit einer ersten axialen Stufe (20), umfassend eine Brennkammer (3) mit einer Brennkammerquerschnittsfläche und eine Anzahl von in der Brennkammer angeordneten Strahldüsen (8, 8', 8") mit einer Strahldüsengesamtaustrittsquerschnittsfläche, wobei eine zweite axiale Stufe (21) mit Luftdüsen (22) der ersten axialen Stufe (20) in Strömungsrichtung eines Verbrennungsgases nachgeschaltet ist und die Strahldüsen (8, 8', 8") so ausgebildet sind, dass ein Verhältnis von Brennkammerquerschnittsfläche zu Strahldüsengesamtaustrittsquerschnittsfläche mindestens 6 beträgt. Die Erfindung betrifft ferner eine Gasturbine.
IPC 8 full level
CPC (source: EP)
F23R 3/06 (2013.01); F23R 3/346 (2013.01); F23R 2900/03282 (2013.01)
Citation (search report)
- [Y] EP 2208935 A1 20100721 - SIEMENS AG [DE]
- [Y] US 2008264033 A1 20081030 - LACY BENJAMIN PAUL [US], et al
- [A] US 2009071157 A1 20090319 - CAI WEIDONG [US]
- [A] US 4408461 A 19831011 - BRUEHWILER EDUARD [CH], et al
- [A] US 5339635 A 19940823 - IWAI YASUO [JP], et al
Designated contracting state (EPC)
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
Designated extension state (EPC)
BA ME
DOCDB simple family (publication)
DOCDB simple family (application)
EP 10187400 A 20101013