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11 条记录 (耗时 0.01 秒)

    Abradable seals
    1.
    发明授权
    Abradable seals 有权
    耐磨密封

    公开(公告)号：US06644914B2

    公开(公告)日：2003-11-11

    申请号：US09815041

    申请日：2001-03-23

    申请人： Steven D Lawer ,  Mark A Halliwell

    发明人： Steven D Lawer ,  Mark A Halliwell

    IPC分类号： F01D1112

    CPC分类号： B23H9/10 ,  F01D11/12 ,  F16J15/445 ,  Y10T29/49297

    摘要： A sealing element (30) for a turbine of a gas turbine engine includes a radially inner surface region provided with an integrally formed seal structure (38) comprising a plurality of radially inwardly projecting walls (40). The walls may be abradable and may define cells (44) for receiving an abradable sealing material.

    摘要翻译： 用于燃气涡轮发动机的涡轮机的密封元件（30）包括设置有整体形成的密封结构（38）的径向内表面区域，所述密封结构（38）包括多个径向向内突出的壁（40）。 壁可以是可磨损的并且可以限定用于接收可磨损的密封材料的电池（44）。

    Stationary blade shroud of a gas turbine
    3.
    发明授权
    Stationary blade shroud of a gas turbine 有权
    燃气轮机的固定叶片护罩

    公开(公告)号：US06692227B2

    公开(公告)日：2004-02-17

    申请号：US10025533

    申请日：2001-12-26

    申请人： Yasuoki Tomita ,  Masamitsu Kuwabara ,  Shunsuke Torii

    发明人： Yasuoki Tomita ,  Masamitsu Kuwabara ,  Shunsuke Torii

    IPC分类号： F01D1112

    CPC分类号： F01D5/225 ,  F01D11/001 ,  F01D11/005

    摘要： A base plate and honeycomb member disposed at the inner circumference side of an inside shroud are fixed to the inside shroud, at a phase deviation in the peripheral direction, with respect to the inside shroud, so as to plug the missing range of seal member, out of gaps between adjacent inside shrouds, and therefore leakage of purge air from the missing range of seal member is prevented without adding new constituent members.

    摘要翻译： 设置在内侧护罩的内周侧的基板和蜂窝构件相对于内侧护罩以周向的相位偏移固定在内侧护罩上，从而堵塞密封构件的缺失范围， 在相邻的内部护罩之间的间隙之外，并且因此防止吹扫空气从密封构件的缺失范围泄漏，而不添加新的构成构件。

    Gas turbine seal
    4.
    发明授权
    Gas turbine seal 有权
    燃气轮机密封

    公开(公告)号：US06652227B2

    公开(公告)日：2003-11-25

    申请号：US10131124

    申请日：2002-04-25

    申请人： Reinhard Fried

    发明人： Reinhard Fried

    IPC分类号： F01D1112

    CPC分类号： F01D11/125 ,  F01D11/122 ,  Y02T50/67

    摘要： The invention relates to a gas turbine seal, comprising a metallic component (1) with a durable or erosion-resistant ceramic coating (2) and an abradable ceramic layer (18) which is arranged thereon in locally delimited fashion, a bond layer (5) being arranged on the surface (4) of the metallic component (1), to which bond layer the durable or erosion-resistant ceramic coating (2) is applied as a covering layer. The invention is characterized in that the bond layer (5) comprises separate, adjacent spherical rivets (6) or mushroom-shaped rivets (6) which have a web (7) and a head (8). These rivets form individual metal islands with numerous undercuts (12), around which there is a continuous ceramic network. It is possible to produce very thick layers which have a good bond strength, the ceramic not being flaked away even in the event of introduction of radial/tangential forces, sickle-shaped contact or locally high overheating/frictional heat, and a good sealing action being achieved.

    摘要翻译： 本发明涉及一种燃气轮机密封件，其包括具有耐久或耐腐蚀陶瓷涂层（2）的金属部件（1）和以局部限制的方式布置在其上的可磨损陶瓷层（18），接合层（5 ）布置在金属部件（1）的表面（4）上，作为覆盖层施加耐用或耐腐蚀陶瓷涂层（2）的粘结层。 本发明的特征在于，接合层（5）包括具有腹板（7）和头部（8）的分离的相邻球形铆钉（6）或蘑菇形铆钉（6）。 这些铆钉形成具有多个底切（12）的独立金属岛，其周围有一个连续的陶瓷网。 可以生产具有良好粘合强度的非常厚的层，即使在引入径向/切向力，镰刀形接触或局部高过热/摩擦热的情况下陶瓷也不会剥落，并且具有良好的密封作用 正在实现。

    Method and apparatus for eliminating thermal bowing using brush seals in the diaphragm packing area of steam turbines
    6.
    发明授权
    Method and apparatus for eliminating thermal bowing using brush seals in the diaphragm packing area of steam turbines 有权
    使用蒸汽轮机隔膜包装区域中的刷密封消除热弯的方法和装置

    公开(公告)号：US06589012B2

    公开(公告)日：2003-07-08

    申请号：US09960672

    申请日：2001-09-24

    申请人： Mark Edward Burnett ,  Christopher Edward Wolfe ,  Frederick George Baily ,  Norman Arnold Turnquist ,  Bruce William Brisson ,  David Alan Caruso

    发明人： Mark Edward Burnett ,  Christopher Edward Wolfe ,  Frederick George Baily ,  Norman Arnold Turnquist ,  Bruce William Brisson ,  David Alan Caruso

    IPC分类号： F01D1112

    CPC分类号： F01D11/001

    摘要： In a steam turbine, a combined brush and labyrinth seal is provided between a diaphragm web and a sealing surface on a rotatable component radially outwardly of the rotor surface. The contact between the brush seal and sealing surface lies along an axially upstream projecting flange of an annular platform such that heat generated by frictional contact between the bristles and the sealing surface has minimal effect on the rotor surface and hence rotor dynamics. A backup labyrinth seal is provided between the web and platform. Additionally, axially upstream projecting flanges are provided on the downstream buckets and which flanges are spaced radially outwardly of the rotor surface and lie in registration with the diaphragm web. Labyrinth teeth seal between the diaphragm web and the bucket flanges serving as a backup seal.

    摘要翻译： 在蒸汽涡轮机中，组合的刷子和迷宫式密封件设置在隔膜腹板和位于转子表面径向外侧的可旋转部件上的密封表面之间。 刷密封和密封表面之间的接触位于环形平台的轴向上游突出的凸缘处，使得由刷毛和密封表面之间的摩擦接触产生的热量对转子表面和因此的转子动力学具有最小的影响。 在网页和平台之间提供备用迷宫式密封。 此外，轴向上游突出凸缘设置在下游铲斗上，并且哪些凸缘在转子表面的径向外侧间隔开并与隔膜腹板对准。 隔膜腹板和作为备用密封件的铲斗法兰之间的迷宫式牙齿密封。

    Abradable coating for gas turbine walls
    8.
    发明授权
    Abradable coating for gas turbine walls 有权
    用于燃气轮机壁的可磨损涂层

    公开(公告)号：US06830428B2

    公开(公告)日：2004-12-14

    申请号：US10292506

    申请日：2002-11-13

    申请人： Philippe Le Biez ,  Joël Vigneau

    发明人： Philippe Le Biez ,  Joël Vigneau

    IPC分类号： F01D1112

    CPC分类号： F01D11/122 ,  F01D5/20 ,  Y02T50/67

    摘要： The coating of abradable material presents cavities opening out into the surface of the coating, the cavities extending over a fraction of the thickness of the coating and being defined by walls which form a plurality of continuous paths at the inside surface of the annular portion between the axial end faces thereof, and which form an angle of not less than 5° relative to the general direction of end portions of blades that might come into contact with the abradable material.

    摘要翻译： 可磨损材料的涂层呈现出通向涂层表面的空腔，空腔延伸超过涂层厚度的一部分，并由壁形成，该壁在环形部分的内表面之间形成多个连续路径 并且其相对于可能与可磨损材料接触的叶片的端部的总方向形成不小于5°的角度。

    Ceramic matrix composite component for a gas turbine engine
    9.
    发明授权
    Ceramic matrix composite component for a gas turbine engine 有权
    用于燃气涡轮发动机的陶瓷基复合材料组件

    公开(公告)号：US06758653B2

    公开(公告)日：2004-07-06

    申请号：US10237769

    申请日：2002-09-09

    申请人： Jay Morrison

    发明人： Jay Morrison

    IPC分类号： F01D1112

    CPC分类号： F01D25/12 ,  F01D9/04 ,  F01D11/18

    摘要： A ceramic matrix composite (CMC) component for a combustion turbine engine (10). A blade shroud assembly (30) may be formed to include a CMC member (32) supported from a metal support member (32). The CMC member includes arcuate portions (50, 52) shaped to surround extending portions (46, 48) of the support member to insulate the metal support member from hot combustion gas (16). The use of a low thermal conductivity CMC material allows the metal support member to be in direct contact with the CMC material. The gap (42) between the CMC member and the support member is kept purposefully small to limit the stress developed in the CMC member when it is deflected against the support member by the force of a rubbing blade tip (14). Changes in the gap dimension resulting from differential thermal growth may be regulated by selecting an angle (A) of a tapered slot (76) defined by the arcuate portion.

    摘要翻译： 一种用于燃气涡轮发动机（10）的陶瓷基体复合材料（CMC）组件。 叶片护罩组件（30）可以形成为包括从金属支撑构件（32）支撑的CMC构件（32）。 CMC构件包括成形为围绕支撑构件的延伸部分（46,48）的弓形部分（50,52），以使金属支撑构件与热燃烧气体（16）绝缘。 使用低导热性CMC材料允许金属支撑构件与CMC材料直接接触。 CMC构件和支撑构件之间的间隙（42）被有目的地保持小，以限制当CMC构件通过摩擦叶片尖端（14）的力而偏转抵靠支撑构件时产生的应力。 可以通过选择由弧形部分限定的锥形槽（76）的角度（A）来调节由差分热生长引起的间隙尺寸的变化。