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4 条记录 (耗时 0.014 秒)

    Uniform effusion cooling method for a can combustion chamber
    1.
    发明申请
    Uniform effusion cooling method for a can combustion chamber 审中-公开
    罐式燃烧室均匀喷射冷却方法

    公开(公告)号：US20050241316A1

    公开(公告)日：2005-11-03

    申请号：US10835169

    申请日：2004-04-28

    申请人： Ly Nguyen ,  Stony Kujala ,  David Walhood ,  Ian Critchley ,  Gregory Woodcock ,  Jurgen Schumacher

    发明人： Ly Nguyen ,  Stony Kujala ,  David Walhood ,  Ian Critchley ,  Gregory Woodcock ,  Jurgen Schumacher

    IPC分类号： F02C3/14 ,  F23R3/10

    CPC分类号： F23R3/10 ,  F23R2900/03041 ,  Y02T50/675

    摘要： A dome for a combustion chamber may have a plurality of effusion holes therein to provide efficient cooling while preventing carbon formation on the dome and chamber walls of the combustion chamber. Conventional dome cooling designs, using dome louvers, for example, may become corroded and/or may allow for ingestion of carbon particles that may build up and eventually separate from the dome. Furthermore, the dome cooling design of the present invention allows for the use of a lower profile dome as compared with conventional domes, thereby maximizing liner volume in the constrained combustion envelope while reducing combustor case weight. Additionally, the dome effusion cooling design of the present invention requires the use of less thermal barrier coating, as compared to conventional designs, in order to minimize thermal variation within the dome and between the dome and the combustor wall. A method for uniformly cooling a dome of a combustion chamber of an engine is also disclosed.

    摘要翻译： 用于燃烧室的圆顶可以在其中具有多个渗出孔以提供有效的冷却，同时防止燃烧室的圆顶和室壁上的碳形成。 例如，使用圆顶百叶窗的常规圆顶冷却设计可能被腐蚀和/或可能允许摄取可能积聚并最终与圆顶分离的碳颗粒。 此外，本发明的圆顶冷却设计允许与常规圆顶相比使用下部轮廓圆顶，由此在减小燃烧器壳体重量的同时最大化受限燃烧包层中的衬管体积。 此外，与传统设计相比，本发明的圆顶渗出冷却设计需要使用较少的热障涂层，以便最小化圆顶内部和圆顶与燃烧室壁之间的热变化。 还公开了一种用于均匀冷却发动机的燃烧室的圆顶的方法。

    Thermally stabilized turbine scroll retention ring for uniform loading application
    2.
    发明申请
    Thermally stabilized turbine scroll retention ring for uniform loading application 失效
    用于均匀加载应用的热稳定型涡轮涡旋保持环

    公开(公告)号：US20050100441A1

    公开(公告)日：2005-05-12

    申请号：US10712434

    申请日：2003-11-12

    申请人： Ly Nguyen ,  James Hadder ,  Gregory Woodcock ,  Stony Kujala

    发明人： Ly Nguyen ,  James Hadder ,  Gregory Woodcock ,  Stony Kujala

    IPC分类号： F01D9/02 ,  F01D9/04 ,  F01D1/02

    CPC分类号： F01D9/026 ,  F01D9/045 ,  F05D2230/642

    摘要： A turbine scroll retention ring may comprise a retainer ring, a plurality of ring fingers, and a plurality of ring joggles. The turbine scroll retention ring may surround and be attached to a radial nozzle. The ring joggles may allow for thermal growth variations between the radial nozzle and the turbine scroll retention ring. The radially outer end portions of the ring fingers may be in contact with a turbine scroll component (for example, an aft scroll ring), such that the turbine scroll retention ring may force contact between the turbine scroll component and the radial nozzle. The finger joggles of the ring fingers may allow for thermal growth variations between the radial nozzle and the turbine scroll component. The turbine scroll retention ring may provide constant axial loading to the aft scroll ring during all engine operating conditions.

    摘要翻译： 涡轮机涡旋保持环可以包括保持环，多个无名指和多个环形滑轨。 涡轮机涡旋保持环可围绕并附接到径向喷嘴。 环形滑轨可以允许径向喷嘴和涡轮涡旋保持环之间的热生长变化。 环形指状物的径向外端部分可以与涡轮机涡旋部件（例如，后涡旋环）接触，使得涡轮涡旋保持环可以迫使涡轮机涡旋部件和径向喷嘴之间的接触。 环形指状物的手指可以允许径向喷嘴和涡轮机涡旋部件之间的热生长变化。 涡轮机涡旋保持环可以在所有发动机操作条件期间为后涡旋环提供恒定的轴向负载。

    Multi-action on multi-surface seal with turbine scroll retention method in gas turbine engine
    3.
    发明申请
    Multi-action on multi-surface seal with turbine scroll retention method in gas turbine engine 失效
    多功能多功能涡轮发动机涡轮涡轮保持法多表面密封

    公开(公告)号：US20050076643A1

    公开(公告)日：2005-04-14

    申请号：US10682217

    申请日：2003-10-08

    申请人： Ly Nguyen ,  Gregory Woodcock ,  Stony Kujala

    发明人： Ly Nguyen ,  Gregory Woodcock ,  Stony Kujala

    IPC分类号： F23R3/50 ,  F23R3/52 ,  F23R3/54 ,  F23R3/60 ,  F02C7/00

    CPC分类号： F23R3/54 ,  F23R3/50 ,  F23R3/52 ,  F23R3/60

    摘要： A gas turbine engine comprises a turbine scroll inside a combustor housing, discouragers with 90-degree bending angles, a radial nozzle contacting a forward bayonet on the forward side of the turbine scroll at a bayonet engagement point and a B-width measured between the discouragers. Retaining ring maintains the size of the B-width. The turbine scroll may have eight surfaces sealing at four locations and a provision to maintain constant “B-width” for the thin sheet metal scroll within the combustion system. The design allows the scroll to operate at high temperature while maintaining lowest possible thermal and mechanical stresses. It can be easily assembled with excellent capability to control gas leakage and minimal component interface wearing or fretting. The gas turbine engine is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially high performance, high cycle flight vehicles.

    摘要翻译： 燃气涡轮发动机包括在燃烧器壳体内的涡轮机涡旋件，具有90度弯曲角度的气门，在卡口接合点处与涡轮机涡旋体的前侧接触前方卡口的径向喷嘴和在气门机构之间测量的B宽度 。 保持环保持B宽度的大小。 涡轮机涡旋件可以在四个位置处具有八个表面密封，并且在燃烧系统内为薄板金属涡卷保持恒定的“B宽度”。 该设计允许滚动体在高温下运行，同时保持尽可能低的热和机械应力。 它可以很容易地组装，具有极好的控制气体泄漏的能力和最小的组件界面磨损或微动。 燃气涡轮发动机适用于飞机，航天器，导弹和其他飞行器，特别是高性能，高周期的飞行器。