ATBECHDEDKESFRGBGRITLILUNLSEMCPTIESILTLVFIROMKCYALTRBGCZEEHUPLSKBAHRIS..MTNORSMESM..................JDIM360 Ver 2.40 (30 Jan 2013) - 1620000/02515042EUROPEAN PATENT APPLICATIONA320140108EP12164848.920120419enenen20111309234520110422US2014010820140220121024201243F23R 3/14 20060101AFI20131203BHEP F23R 3/28 20060101ALI20131203BHEP deAerodynamische KraftstoffdüseenAerodynamic fuel nozzlefrBuse à combustible aérodynamique4General Electric Company101056012226854/177331 River RoadSchenectady, NY 12345USHaynes, Joel Meier1 Research Circle Building K1-3A59Niskayuna, NY New York 12309USCleary, Fidelma101356232GPO Europe GE International Inc. The Ark 201 Talgarth Road HammersmithLondon W6 8BJGBALATBEBGCHCYCZDEDKEEESFIFRGBGRHRHUIEISITLILTLULVMCMKMTNLNOPLPTRORSSESISKSMTRBAME20140108201402

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).

226854/17733EP12164848.9General Electric Company4MN20131209F23REP1909032A2GEN ELECTRIC [US]20080409X1-15* column 5, lines 1-7 ** column 5, lines 38-45 ** column 5, lines 9-15 ** figures 2,3 *US7631500B2MUELLER MARK ANTHONY [US] ET AL20091215X1-15* figure 4 *US2010126176A1KIM IK SOO [GB]20100527X1-15* the whole document *US6389815B1HURA HARJIT SINGH [US] ET AL20020521X1-15* the whole document *Christen, JérômeMunich20131129EP1909032A220080409CN101158476A20080409EP1909032A220080409JP2008096099A20080424US2008083224A120080410US7631500B220091215CA2603567A120080329EP1909030A220080409JP4958709B220120620JP2008089296A20080417US2008078181A120080403US2010126176A120100527EP2192347A120100602US2010126176A120100527US6389815B120020521EP1186832A220020313JP4800523B220111026JP2002139221A20020517US6389815B120020521