ANTI-FLASHBACK FEATURES IN GAS TURBINE ENGINE COMBUSTORS
摘要
A gas turbine combustor (10) comprises a base plate (12) from which protrude a plurality of lips (36) that surround respective apertures (16) into which are positioned downstream ends (19) of main swirler assemblies (18). The apertures (16) are arranged about a centrally positioned pilot cone (22) that comprises an inner cone (23) and an outer cone (25), defining a space (31) there between. A number of laterally directed apertures (60) are disposed along the outer cone (25) so as to direct a flow of fluid toward a near portion (38) of each lip (36), thereby perturbing pockets of high fuel-to-air mixtures between the outer cone (25) and the near region (38). The provision of such laterally directed apertures (60) reduces or eliminates flashback between the outer cone (25) and the near region (38) through such action.
申请公布号
WO2009005516(A2)
申请公布日期
2009.01.08
申请号
WO2007US24260
申请日期
2007.11.20
申请人
SIEMENS ENERGY, INC.;HARRIS, JR., ARTHUR J.;OHRI, RAJEEV