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38 条记录 (耗时 0.037 秒)

    Methods and apparatus for regulating turbine clearance control system airflow
    2.
    发明授权
    Methods and apparatus for regulating turbine clearance control system airflow 有权
    调节涡轮间隙控制系统气流的方法和装置

    公开(公告)号：US06722137B2

    公开(公告)日：2004-04-20

    申请号：US09932596

    申请日：2001-08-17

    申请人： Robert Proctor ,  John William Hanify ,  Debra Lynn Prikkel ,  Michael Jay Epstein ,  Julius John Montgomery

    发明人： Robert Proctor ,  John William Hanify ,  Debra Lynn Prikkel ,  Michael Jay Epstein ,  Julius John Montgomery

    IPC分类号： F16K122

    CPC分类号： F16K1/222 ,  F01D17/148

    摘要： A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides.

    摘要翻译： 用于燃气涡轮发动机的蝶形阀包括阀轴和阀盘。 阀盘具有延伸穿过阀盘的中心线。 阀盘还包括轴开口，外周边，外表面，第一侧和第二侧。 第一面与第二面相对。 轴开口延伸穿过邻近中心线轴线的阀盘，并且其尺寸被设计成在其中容纳阀轴。 盘外表面在第一和第二侧上延伸，并且在圆盘第一和第二面中的至少一个之间在外圆周和中心线轴线之间呈锥形。

    Brush seal segment having bristle damping
    6.
    发明授权
    Brush seal segment having bristle damping 失效
    刷子密封段具有刷毛阻尼

    公开(公告)号：US06293554B1

    公开(公告)日：2001-09-25

    申请号：US09451246

    申请日：1999-11-29

    申请人： Osman Saim Dinc ,  Yahya Dogu ,  Michael Eugene Battle ,  Robert Joseph Albers ,  Robert Proctor

    发明人： Osman Saim Dinc ,  Yahya Dogu ,  Michael Eugene Battle ,  Robert Joseph Albers ,  Robert Proctor

    IPC分类号： F16J15447

    CPC分类号： F16J15/3288

    摘要： A brush seal segment useful, when circumferentially arrayed with other such segments, to seal the gap between a rotor and a surrounding casing of a rotary machine such as a gas or steam turbine. Brush-seal bristles are positioned between a brush-seal back plate and a brush-seal front plate with the free end of each bristle extending beyond the edges of the plates. The front plate has a portion extending to the edge of the front plate with the portion spaced apart from the bristles. In one example, the portion has an array of through holes. In another example, the portion has a ledge projecting generally away from the bristles.

    摘要翻译： 当用其它这种部分周向排列时，用于密封旋转机器诸如气体或汽轮机的转子和周围壳体之间的间隙的刷密封段是有用的。 刷密封刷毛位于刷密封背板和刷密封前板之间，每个刷毛的自由端延伸超过板的边缘。 前板具有延伸到前板的边缘的部分，其中与刷毛间隔开的部分。 在一个示例中，该部分具有通孔阵列。 在另一个示例中，该部分具有大致远离刷毛突出的突出部。

    Shroud cooling assembly for gas turbine engine
    7.
    发明授权
    Shroud cooling assembly for gas turbine engine 有权
    燃气轮机发动机护罩冷却组件

    公开(公告)号：US06139257A

    公开(公告)日：2000-10-31

    申请号：US249205

    申请日：1999-02-12

    申请人： Robert Proctor ,  Edward P. Brill ,  Randall B. Rydbeck ,  John W. Hanify ,  Gregory A. White

    发明人： Robert Proctor ,  Edward P. Brill ,  Randall B. Rydbeck ,  John W. Hanify ,  Gregory A. White

    IPC分类号： F01D11/02 ,  F01D9/04 ,  F01D25/12 ,  F02C7/18 ,  F01D25/08

    CPC分类号： F01D11/08 ,  F01D9/04 ,  F05D2260/201 ,  F05D2260/202

    摘要： To cool the shroud assembly in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow to baffle plenums and thence through baffle perforations to impingement cool the rails and back surfaces of the shroud. Impingement cooling air then flows through elongated, convection cooling passages in the shroud sections and exits to flow along the shroud front surface with the main gas stream to provide film cooling. The aft rail of the shroud sections is provided with one or more cooling holes to impingement cool the annular retaining ring or C-clip retaining the shroud sections on the shroud hangers. This cooling air then travels aftward on the inboard side of the C-clip to provide convection cooling of the C-clip. In an alternative embodiment, cooling air is directed at the aft corners of the shroud base to avoid overheating.

    摘要翻译： 为了冷却燃气轮机发动机的高压涡轮机部分中的护罩组件，将高压冷却空气以计量流量导向挡板增压室，从而通过挡板穿孔冲击以冷却护罩的轨道和后表面。 冲击冷却空气然后流过护罩部分中的细长的对流冷却通道并且离开以沿着护罩前表面与主气流一起流动以提供膜冷却。 护罩部分的后导轨设置有一个或多个冷却孔，以将保持护罩部分的环形固定环或C形夹子冷却到护罩悬挂器上。 然后，该冷却空气在C形夹的内侧向后行进，以提供C形夹的对流冷却。 在替代实施例中，冷却空气被引导到护罩底座的后角以避免过热。

    Smart turbine shroud
    8.
    发明授权
    Smart turbine shroud 失效
    智能涡轮罩

    公开(公告)号：US5593277A

    公开(公告)日：1997-01-14

    申请号：US467418

    申请日：1995-06-06

    申请人： Robert Proctor ,  David R. Linger ,  David A. Di Salle ,  Steven R. Brassfield ,  Larry W. Plemmons

    发明人： Robert Proctor ,  David R. Linger ,  David A. Di Salle ,  Steven R. Brassfield ,  Larry W. Plemmons

    IPC分类号： F01D11/18 ,  F01D11/24

    CPC分类号： F01D11/18 ,  F01D11/24

    摘要： A turbine shroud includes an annular outer casing having first and second radial flanges between which are suspended an adjoining annular shroud support and an annular shroud hanger. A plurality of shroud panels are joined to the shroud hanger and are positionable radially above turbine rotor blades to define a tip clearance therebetween. The four flanges are disposed in abutting contact with each other, and respective pluralities of circumferentially spaced apart first, second, and third recesses are disposed respectively between the casing first flange and the shroud flange, between the shroud flange and the hanger flange, and between the hanger flange and the casing second flange for providing radial flowpaths therebetween. The support flange and the hanger flange have respective pluralities of circumferentially spaced apart first and second metering holes extending axially therethrough for providing flow communication between the first, second, and third recesses for channeling compressor bleed air therethrough for controlling the tip clearance.

    摘要翻译： 涡轮机护罩包括具有第一和第二径向凸缘的环形外壳，在其之间悬挂有邻接的环形护罩支撑件和环形护罩悬挂器。 多个护罩板连接到护罩悬挂器并且可径向地位于涡轮转子叶片上方以限定其间的顶端间隙。 四个凸缘彼此邻接地设置，并且相应的多个周向间隔开的第一，第二和第三凹槽分别设置在壳体第一凸缘和护罩凸缘之间，护罩凸缘和悬挂器凸缘之间，以及 衣架法兰和套管第二法兰，用于在其间提供径向流动路径。 支撑凸缘和悬挂器法兰具有相应的多个周向间隔开的第一和第二计量孔，其轴向延伸穿过其中，以提供第一，第二和第三凹部之间的流动连通，用于引导压缩机排出空气通过其中以控制顶端间隙。

    Air-oil separator
    10.
    发明授权
    Air-oil separator 有权
    空气油分离器

    公开(公告)号：US08292034B2

    公开(公告)日：2012-10-23

    申请号：US11946103

    申请日：2007-11-28

    申请人： James Kevin Mount ,  Richard Walker Nicholson ,  Duane Howard Anstead ,  Robert Proctor ,  Pradeep Hemant Sangli ,  Prasad Laxman Kane ,  Mark Leonard Hopper

    发明人： James Kevin Mount ,  Richard Walker Nicholson ,  Duane Howard Anstead ,  Robert Proctor ,  Pradeep Hemant Sangli ,  Prasad Laxman Kane ,  Mark Leonard Hopper

    IPC分类号： B05B12/00

    CPC分类号： F01D25/18

    摘要： The present invention provides an air-oil separator comprising a first region having a mixture of air and oil, a second region wherein separation of at least some of the oil from the air-oil mixture occurs and at least one multi-directional injector plug located on a rotating component in flow communication with the first region and the second region, the multi-directional injector plug having a discharge head that is oriented such that at least a part of the air-oil mixture discharged therefrom has a component of velocity that is tangential to the direction of rotation of the rotating component.

    摘要翻译： 本发明提供了一种空气 - 油分离器，其包括具有空气和油的混合物的第一区域，其中至少一部分油与空气 - 油混合物分离的第二区域和至少一个多向注入塞 在与第一区域和第二区域流动连通的旋转部件上，多向注入器插头具有排出头，该排出头被定向成使得从其排出的空气 - 油混合物的至少一部分具有速度分量 与旋转部件的旋转方向相切。