(19)
(11) EP 2 515 042 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
08.01.2014 Bulletin 2014/02

(43) Date of publication A2:
24.10.2012 Bulletin 2012/43

(21) Application number: 12164848.9

(22) Date of filing: 19.04.2012
(51) International Patent Classification (IPC): 
F23R 3/14(2006.01)
 F23R 3/28(2006.01)
(84) Designated Contracting States:
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 States:
BA ME

(30) Priority: 22.04.2011 US 201113092345

(71) Applicant: General Electric Company
Schenectady, NY 12345 (US)

(72) Inventor:
  • Haynes, Joel Meier
    Niskayuna, NY New York 12309 (US)

(74) Representative: Cleary, Fidelma 
GPO Europe GE International Inc. The Ark 201 Talgarth Road Hammersmith
London W6 8BJ
London W6 8BJ (GB)

   


(54) Aerodynamic fuel nozzle


(57) The present application and the resultant patent provide a combustor (100) for a turbine engine (10). The combustor (100) may include a number of fuel nozzles (110) with one or more of the fuel nozzles (110) including a swirler assembly (130). The swirler assembly (130) may include a number of stages (140) with a number of fueled structures (245) and a number of unfueled structures (250).







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