发明名称 Turbine engine fuel nozzle
摘要 A performance-enhancing fuel nozzle is disclosed. The nozzle suitable for use in combustors which combine high-swirl-number combustion in a pilot zone with low-swirl-number combustion in a main combustion zone. The nozzle includes a fuel delivery member adapted for fluid communication with a fuel source and a flow conditioning member having a fuel exit port. The fuel exit port is in fluid communication with the fuel supply and is adapted to ensure that the recirculation region adjacent the nozzle tip remains flame free. In one aspect of the invention, the fuel concentration profile of the nozzle is characterized by a radially-outward region that is flammable and a radially-inward region that is substantially non-flammable. In another aspect of the invention, the fuel exit port being is disposed a radially-outward portion of the flow conditioning member. In another aspect of the invention, the flow conditioning member is characterized by a swirl number lower than about 0.5. In another aspect of the invention, the exit are high-momentum jets, having a design ratio pressure of greater than about 1.1. In another aspect of the invention, the nozzle is part of a combustor which has a high-swirl-number combustion in a pilot zone and low-swirl-number combustion in a main combustion zone.
申请公布号 US6832481(B2) 申请公布日期 2004.12.21
申请号 US20020255892 申请日期 2002.09.26
申请人 SIEMENS WESTINGHOUSE POWER CORPORATION 发明人 KOENIG MICHAEL HERBERT;PRADE BERND
分类号 F23R3/14;F23R3/28;(IPC1-7):F23R3/30 主分类号 F23R3/14
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