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    • 10. 发明公开
    • Nozzle for diffusion and premix combustion in a turbine
    • Düsezur Diffusions- und Vormischverbrennung in einer Turbine
    • EP0800038A2
    • 1997-10-08
    • EP97302181.9
    • 1997-03-27
    • GENERAL ELECTRIC COMPANY
    • Mick, Warren J.Sciochetti, Michael BruceDavis, Lewis Berkley, Jr.Fitts, David Orus
    • F23D14/82F23D14/48F23D14/02F23D14/24
    • F23D14/22F23D14/02F23D14/48F23D14/82F23D2206/10F23D2211/00F23D2900/00008
    • A fuel nozzle for a gas turbine includes a nozzle body (56) having a tip portion (82), the nozzle body including an inner tube (72) defining an axially extending air passage (73); an intermediate tube (74) concentrically arranged and radially spaced from the inner tube and defining a diffusion fuel passage (76) therebetween; and an outer tube (78) concentrically arranged and radially spaced from the intermediate tube and defining a premix fuel passage (80) therebetween. The outer tube has a plurality of radially extending injectors (68) in communication with the premix fuel passage. The premix fuel passage is further defined in part by an outer tube wall portion (92) formed with at least one weakened region (94) adapted to burn through in the event of a flashback, thereby causing a substantial portion of premix fuel to bypass the injectors and to exit the nozzle body at the at least one weakened region.
    • 一种用于燃气轮机的燃料喷嘴包括具有尖端部分(82)的喷嘴体(56),所述喷嘴体包括限定轴向延伸空气通道(73)的内管(72)。 同心地布置并与内管径向间隔开并在其间限定扩散燃料通道(76)的中间管(74); 和与所述中间管径向间隔开并在其间限定预混合燃料通道(80)的外管(78)。 外管具有与预混合燃料通道连通的多个径向延伸的喷射器(68)。 预混燃料通道的另一部分由外管壁部分(92)限定,所述外管壁部分(92)形成有至少一个弱化区域(94),该弱化区域(94)在闪回的情况下适于燃烧,从而使大部分预混燃料绕过 并且在至少一个弱化区域处离开喷嘴体。