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    • 1. 发明申请
    • Combustor flow sleeve attachment system
    • 燃烧器流套管附件系统
    • US20070130958A1
    • 2007-06-14
    • US11298323
    • 2005-12-08
    • Rajeev OhriArthur HarrisElliot GriffinMichael KoenigHerbert ReidPaul Maples
    • Rajeev OhriArthur HarrisElliot GriffinMichael KoenigHerbert ReidPaul Maples
    • F23R3/60
    • F23R3/60
    • Embodiments of the invention relate to a combustor flow sleeve for a turbine engine. According to aspects of the invention, the flow sleeve can be attached to one of the components in the combustor head-end by a plurality of fasteners. In one embodiment, the flow sleeve can be attached directly to the combustor head-end component by a plurality of bolts. The bolted flow sleeve can reduce the time to install or remove the flow sleeve. In certain areas, it may not be possible to directly attach the flow sleeve to the combustor component. A flow sleeve according to aspects of the invention can be adapted to facilitate indirect attachment to the combustor head-end component. The flow sleeve can further be adapted to include thermal relief slots to accommodate any differential thermal expansion or contraction between the flow sleeve and the component to which the flow sleeve is attached.
    • 本发明的实施例涉及一种用于涡轮发动机的燃烧器流动套筒。 根据本发明的方面,流动套管可以通过多个紧固件附接到燃烧器头端中的一个部件。 在一个实施例中,流动套筒可以通过多个螺栓直接附接到燃烧器头端部件。 螺栓流动套筒可以减少安装或拆卸流动套管的时间。 在某些区域中,可能不可能将流动套筒直接附接到燃烧器部件。 根据本发明的方面的流动套筒可以适于促进间接地连接到燃烧器头端部件。 流动套管还可以适于包括热释放槽,以适应流动套筒与流动套筒所附接的部件之间的任何不同的热膨胀或收缩。
    • 2. 发明申请
    • Swirler assembly and combinations of same in gas turbine engine combustors
    • 涡轮组件及其在燃气轮机发动机燃烧器中的组合
    • US20070000228A1
    • 2007-01-04
    • US11169478
    • 2005-06-29
    • Rajeev OhriKristian WetzlHerbert ReidArthur HarrisDavid ParkerStephen Mumford
    • Rajeev OhriKristian WetzlHerbert ReidArthur HarrisDavid ParkerStephen Mumford
    • F02C3/14
    • F23R3/14
    • A fuel/air mixing apparatus, such as a main swirler assembly (400) comprising a sleeve (410), provides for additional air entry around the perimeter of a bore (440) through which passes a fuel/air mixture. The additional air reduces or eliminates flashback during operation of a gas turbine comprising the assembly (400). In some embodiments, a plurality of gaps (464) exists between spaced apart tabs (462) along a downstream end (460) of the sleeve (410). During gas turbine operation, air flows through both a flashback annulus (411) and the gaps (464). In other embodiments, a plurality of holes are placed upstream and in line with the tabs (1004) to supplement the air flow through gaps (1006). In yet other embodiments, rows (1102) of holes (1104) are provided to supplement the airflow. Downstream ends (460,1218) may interface with a downstream-oriented lip (460) or with an upstream-oriented lip (1224). The interfacing may comprise a fit effective to damp vibration and to increase the natural frequency.
    • 诸如包括套筒(410)的主旋流器组件(400)的燃料/空气混合设备提供围绕通过燃料/空气混合物的孔(440)的周边的附加空气进入。 在包括组件(400)的燃气涡轮机的操作期间,附加空气减少或消除了回火。 在一些实施例中,沿着套筒(410)的下游端(460)的间隔开的突片(462)之间存在多个间隙(464)。 在燃气轮机操作期间,空气流过回流环(411)和间隙(464)。 在其他实施例中,多个孔被放置在上游并且与突片(1004)成一直线,以补充通过间隙(1006)的空气流。 在其它实施例中,提供孔(1104)的孔(1104)以补充气流。 下游端(460,1218)可以与下游定向的唇缘(460)或与上游取向唇缘(1224)相接触。 接口可以包括有效地阻尼振动并增加固有频率的配合。