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43 条记录 (耗时 0.018 秒)

    Advanced quench pattern combustor
    3.
    发明公开
    Advanced quench pattern combustor 审中-公开
    Brennkammer mit verbesserter Anordnung vonLöschlöchern

    公开(公告)号：EP2253887A2

    公开(公告)日：2010-11-24

    申请号：EP10163039.0

    申请日：2010-05-17

    申请人： United Technologies Corporation

    发明人： Kim, Won-Wook ,  Snyder, Timothy S.

    IPC分类号： F23R3/06

    CPC分类号： F23R3/06

    摘要： A combustor (20) for a gas turbine engine includes a forward bulkhead (22), an inner radial combustor wall (26) and an outer radial combustor wall (28). The forward bulkhead has a plurality of circumferentially disposed injector apertures (34). The inner radial combustor wall is attached to and extends axially out from the forward bulkhead. The outer radial combustor wall is attached to and extends axially out from the forward bulkhead. At least one of the inner radial combustor wall and the outer radial combustor wall includes a plurality of quench aperture sets. Each quench aperture set includes a plurality of quench apertures. Adjacent quench apertures included within each quench aperture set are separated by an intraset distance. Adjacent quench aperture sets are separated by an interset distance. The intraset distance is different than the interset distance. The outer radial combustor wall is disposed radially outside the inner radial combustor wall, thereby defining an annular combustion region therebetween.

    摘要翻译： 用于燃气涡轮发动机的燃烧器（20）包括前舱壁（22），内径向燃烧器壁（26）和外径向燃烧室壁（28）。 前隔板具有多个周向设置的喷射孔（34）。 内部径向燃烧器壁从前舱壁附接到轴向外延伸。 外部径向燃烧器壁从前舱壁附接到轴向外延伸。 内径向燃烧器壁和外径向燃烧器壁中的至少一个包括多个淬火孔组。 每个淬火孔径组包括多个淬火孔。 每个淬火孔径组件中包括的相邻淬火孔径由一个入口间距离分开。 相邻的淬火孔径组间隔一个间距。 内部距离不同于间距。 外径向燃烧室壁径向设置在内径向燃烧室壁的外侧，从而在其间形成环形燃烧区域。

    Method of combustion with low acoustics
    6.
    发明公开
    Method of combustion with low acoustics 失效
    Verbrennungsverfahren mit geringen akustischenTönen

    公开(公告)号：EP0849531A2

    公开(公告)日：1998-06-24

    申请号：EP97310465.6

    申请日：1997-12-22

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Snyder, Timothy S. ,  Sowa, William A.

    IPC分类号： F23C7/00 ,  F23C9/00

    CPC分类号： F23C9/006 ,  F23C7/002 ,  F23C2202/40 ,  F23C2900/07002 ,  F23D17/002 ,  F23D2206/10 ,  F23D2209/20 ,  F23D2210/00

    摘要： A method of reducing pressure fluctuations in the combustor of a gas turbine engine resulting from the combustion of fuel and air therein comprises combusting a fuel/air mixture in a combustor downstream of the exit plane of a fuel nozzle assembly such that such recirculation zones generated by the fuel nozzle assembly are in spaced relation to the exit plane at all operating conditions of the engine.

    摘要翻译： 一种减少燃料涡轮发动机的燃烧器的燃烧器中由于燃料和空气的燃烧引起的压力波动的方法包括在燃料喷嘴组件的出口平面下游的燃烧器中燃烧燃料/空气混合物，使得由燃料喷嘴组件产生的这种再循环区域 在发动机的所有操作条件下，燃料喷嘴组件与出口平面间隔开。

    Tangential entry fuel nozzle
    7.
    发明公开
    Tangential entry fuel nozzle 失效
    TangentialeBrennstoffeintrittsdüse

    公开(公告)号：EP0849529A2

    公开(公告)日：1998-06-24

    申请号：EP97310463.1

    申请日：1997-12-22

    申请人： UNITED TECHNOLOGIES CORPORATION

    发明人： Snyder, Timothy S. ,  Sowa, William A. ,  Kramer, Stephen K.

    IPC分类号： F23C7/00 ,  F23D17/00

    CPC分类号： F23D17/002 ,  F05B2250/322 ,  F23C7/002 ,  F23C2900/07002

    摘要： A method of reducing the tendency of the combustion flame to attach to the centerbody of a tangential entry nozzle 10 is disclosed which comprises mixing fuel and air in a mixing zone 28 within a fuel nozzle assembly, thereby producing a first fuel/air mixture, which is isolated from the combustion products by maintaining sufficiently high axial velocities throughout the mixing zone.
    The nozzle has a longitudinal axis 26 and two cylindrical-arc scrolls 22,24 with the centerline of each offset from that of the other. Overlapping ends of these scrolls form an air inlet slot therebetween for the introduction of an air/fuel mixture into the fuel nozzle. A combustor-end endplate 18 has a central opening 20 to permit air and fuel to exit into a combustor, while at the opposite end another endplate 16 blocks the nozzle flow area. The scrolls are secured between these endplates. A centerbody 12 is located between the scrolls coaxial with the axis. The centerbody 12 has a base 58 which includes at least one air supply port extending therethrough, and an internal passageway 64. It includes a frustum portion (54) and aerodynamic ramps theat prevent flow reversal and flame stabilisation between the endplates 16,18.

    摘要翻译： 公开了一种降低燃烧火焰附着到切向入口喷嘴10的中心体的趋势的方法，其包括将燃料和空气混合在燃料喷嘴组件内的混合区28中，从而产生第一燃料/空气混合物， 通过在整个混合区域保持足够高的轴向速度与燃烧产物隔离。 喷嘴具有纵向轴线26和两个圆柱形涡卷22,24，其中心线各自偏离另一个。 这些涡卷的重叠端部在其间形成空气入口槽，用于将空气/燃料混合物引入燃料喷嘴。 燃烧器端端板18具有中心开口20，以允许空气和燃料排出到燃烧器中，而在相对端，另一端板16阻挡喷嘴流动区域。 涡卷固定在这些端板之间。 中心体12位于与轴线同轴的涡卷之间。 中心体12具有基部58，其包括延伸穿过其中的至少一个空气供应端口和内部通道64.其包括平截头体部分（54）和空气动力学斜坡，以防止端板16,18之间的流动反转和火焰稳定。