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11.发明授权Pin-loaded mounting apparatus for a refractory component in a combustion turbine engine 失效用于燃气涡轮发动机中的耐火部件的销装载安装装置公开(公告)号：US07563071B2
公开(公告)日：2009-07-21
申请号：US11197233
申请日：2005-08-04
IPC分类号： F01D11/08
CPC分类号： F01D9/04 , F05D2240/11 , F05D2300/21
摘要： An apparatus for mounting a refractory component such as a turbine shroud ring segment (32) with a ceramic core (42) onto a combustion turbine engine structure (34). The ring segment has a ceramic matrix composite skin (40), and optionally, a thermal insulation layer (46). A pin (60) is inserted through a bore (48) in the core and through an attachment bar (54) with ends received in wells (50) in the core. The attachment bar may be attached to a backing member, or tophat (64), by a biasing device (76) that urges the refractory component snugly against the backing member to eliminate vibration. The backing member and refractory component have mating surfaces that may include angled sides (52S, 70). The backing member is attached to the engine structure. Turbine shroud ring segments can be attached by this apparatus to a surrounding structure to form a shroud ring.
摘要翻译： 一种用于将诸如具有陶瓷芯（42）的涡轮机护罩环段（32）的耐火部件安装到燃气涡轮发动机结构（34）上的装置。 所述环段具有陶瓷基复合蒙皮（40），并且可选地具有绝热层（46）。 销（60）通过芯中的孔（48）插入并通过附接杆（54）插入，末端容纳在芯中的孔（50）中。 附接杆可以通过偏压装置（76）附接到背衬构件或托盘（64），偏置装置（76）将耐火构件紧贴地抵靠背衬构件以消除振动。 背衬构件和耐火构件具有可以包括成角度的侧面（52S，70）的配合表面。 背衬构件附接到发动机结构。 涡轮护罩环段可以通过该装置附接到周围结构以形成护罩环。
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公开(公告)号：US07494317B2
公开(公告)日：2009-02-24
申请号：US11165367
申请日：2005-06-23
CPC分类号： F01D11/025 , F01D11/08 , Y02T50/672
摘要： A system for attaching a ring seal to a vane carrier in a turbine engine can allow the ring seal to radially expand and contract at least partially independently of the vane carrier. The system can also be configured to substantially restrict axial and/or circumferential movement of the ring seal. In one embodiment, the ring seal can include a plurality of radial slots circumferentially spaced about the ring seal. A pin can extend substantially through each of the slots and into operative engagement with isolation rings, which are connected to the vane carrier. In another embodiment, the ring seal and the isolation rings can include a series of axially-extending protrusions extending substantially circumferentially about each component. The protrusions on the ring seal can substantially matingly engage the protrusions on the isolation rings. The protrusions can be configured as a Hirth coupling.
摘要翻译： 用于将环形密封件附接到涡轮发动机中的叶片承载件的系统可允许环形密封件至少部分地独立于叶片承载件而径向膨胀和收缩。 该系统还可以构造成基本上限制环形密封件的轴向和/或周向运动。 在一个实施例中，环形密封件可以包括围绕环形密封件周向间隔开的多个径向槽。 销可以基本上延伸穿过每个槽，并且与连接到叶片承载件的隔离环可操作地接合。 在另一个实施例中，环形密封件和隔离环可以包括一系列沿着每个部件大致周向延伸的轴向延伸的突出部。 环形密封件上的突起可以基本配合地接合隔离环上的突起。 突起可以配置为Hirth耦合。
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公开(公告)号：US20120125585A1
公开(公告)日：2012-05-24
申请号：US11715678
申请日：2007-03-08
IPC分类号： F28F1/10
CPC分类号： F28F21/04 , B32B18/00 , C04B35/803 , C04B37/001 , C04B2237/34 , C04B2237/38 , C04B2237/62 , C04B2237/64 , F01D5/187 , F01D5/282 , F05D2260/201 , F28F7/02 , Y10T428/131 , Y10T428/1314 , Y10T428/1317 , Y10T428/1362 , Y10T428/139 , Y10T428/1393 , Y10T428/24521 , Y10T428/24612 , Y10T428/24744 , Y10T442/3195 , Y10T442/3203 , Y10T442/3211
摘要： A ceramic matrix composite wall structure (20A) constructed of interlocking layers (22A, 24A) of woven material with integral cooling channels (28A, 32A). The CMC layer closest to the hot gas path (41) contains internal cooling tubes (26A, 30A) protruding into a ceramic insulating layer (40A). This construction provides a cooled CMC lamellate wall structure with an interlocking truss core.
摘要翻译： 一种由具有整体式冷却通道（28A，32A）的编织材料的互锁层（22A，24A）构成的陶瓷基体复合壁结构（20A）。 最靠近热气体路径（41）的CMC层包含突出到陶瓷绝缘层（40A）中的内部冷却管（26A，30A）。 这种结构提供了具有互锁桁架芯的冷却的CMC层状壁结构。
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公开(公告)号：US07908867B2
公开(公告)日：2011-03-22
申请号：US11855623
申请日：2007-09-14
IPC分类号： F02C1/00
CPC分类号： F01D9/023 , F23R3/007 , Y10T428/1317
摘要： A ceramic hybrid structure (207, 502, 602, 608) that includes a wavy ceramic matrix composite (CMC) wall (214, 532, 603, 609) bonded with a ceramic insulating layer (230, 538, 604, 610) having a distal surface (242) that may define a hot gas passage (250, 550, 650) or otherwise be in proximity to a source of elevated temperature. In various embodiments, the waves (216, 537, 637) of the CMC wall (214, 532, 603, 609) may conform to the following parameters: a thickness (222) between 1 and 10 millimeters; an amplitude (224) between one and 2.5 times the thickness; and a period (226) between one and 20 times the amplitude. The uninsulated backside surface (218) of the CMC wall (214) provides a desired stiffness and strength and enhanced cooling surface area. In various embodiments the amplitude (224), excluding the thickness (222), may be at least 2 mm.
摘要翻译： 一种陶瓷混合结构（207,502,602,608），其包括与陶瓷绝缘层（230,538,604,610）接合的波纹陶瓷基复合材料（CMC）壁（214,532,603,609），其具有 远端表面（242），其可以限定热气体通道（250,550,650）或以其它方式接近升高的温度源。 在各种实施例中，CMC壁（214,532,603,609）的波浪（216,537,637）可以符合以下参数：1和10毫米之间的厚度（222）; 幅度（224）为厚度的1至2.5倍; 以及振幅的1到20倍之间的周期（226）。 CMC壁（214）的未绝缘的背侧表面（218）提供期望的刚度和强度以及增强的冷却表面积。 在各种实施例中，不包括厚度（222）的振幅（224）可以至少为2mm。
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公开(公告)号：US07871244B2
公开(公告)日：2011-01-18
申请号：US11707193
申请日：2007-02-15
IPC分类号： F01D11/12
CPC分类号： F01D11/122 , F05D2230/31 , F05D2230/90 , F05D2240/11 , F05D2240/127 , F05D2250/70 , F05D2250/71 , F05D2250/711 , F05D2260/30 , F05D2300/21
摘要： A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a portion of a gap gas flow path where the inner radial surface may be formed of an abradable ceramic coating and includes a plurality of gas flow protrusions that are oriented transverse to the gap gas flow path. The gas flow protrusions may induce vortices in the gas flow in the gap gas flow path. Additionally, the gas flow protrusions may be series of peaks and depressions between two adjacent peaks, where the depressions have an approximate semicircular shape. The distance between two adjacent peaks may be equal or greater than a width of the depression and the height of a single peak may be six percent or greater than the distance between two adjacent peaks.
摘要翻译： 涡轮发动机环密封件，用于密封涡轮发动机外密封段和涡轮叶片尖端之间的间隙。 涡轮发动机环段可以具有限定间隙气体流动路径的一部分的内部径向表面，其中内部径向表面可以由可磨损陶瓷涂层形成，并且包括多个气体流动突起，其横向于间隙气体 流路。 气流突起可以在间隙气体流动路径中的气流中引起涡流。 此外，气流突起可以是两个相邻峰之间的一系列峰和凹陷，其中凹陷具有近似的半圆形。 两个相邻峰之间的距离可以等于或大于凹陷的宽度，单个峰的高度可以是两个相邻峰之间的距离的6％或更大。
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公开(公告)号：US07726936B2
公开(公告)日：2010-06-01
申请号：US11492590
申请日：2006-07-25
IPC分类号： F04D29/08
CPC分类号： F01D11/12 , F05D2230/60 , F05D2240/11
摘要： Aspects of the invention relate to a ring seal for a turbine engine. The ring seal can be made up of a plurality of circumferentially abutted ring seal segments. Each ring seal segment can comprise a plurality of individual channels. The channels can be generally U-shaped in cross-section with a forward span, and aft span and an extension connecting therebetween. The channels can be positioned such that the aft span of one channel can substantially abut the forward span of another channel. The plurality of separate channels can be detachably coupled to each other by, for example, a plurality of pins. The ring seal segment according to aspects of the invention can facilitate numerous advantageous characteristics including greater material selection, selective cooling, improved serviceability, and reduced blade tip leakage. Moreover, the configuration is well suited to handle the operational loads of the turbine.
摘要翻译： 本发明的方面涉及一种用于涡轮发动机的环形密封件。 环形密封件可以由多个周向邻接的环形密封段组成。 每个环形密封片段可以包括多个单独的通道。 通道可以具有大致U形的横截面，具有前跨距，后跨距和延伸部之间的连接。 通道可以被定位成使得一个通道的后跨距可以基本上抵靠另一通道的前跨。 多个单独的通道可以通过例如多个销可拆卸地彼此联接。 根据本发明的方面的环形密封段可以促进许多有利的特征，包括更大的材料选择，选择性冷却，改进的可使用性和减小的叶片尖端泄漏。 此外，该构造非常适合于处理涡轮机的操作负载。
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公开(公告)号：US07534086B2
公开(公告)日：2009-05-19
申请号：US11418863
申请日：2006-05-05
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F05D2250/70 , F05D2250/712 , F05D2300/21 , F05D2300/603 , F16J15/104
摘要： Aspects of the invention are directed to a multi-layer ring seal segment that can incorporate a plurality of material systems. The ring seal segment can include an inner layer, a central layer and an outer layer. The inner layer can be attached to one side of the central layer, and the outer layer can be attached to an opposite side of the central layer. The inner and outer layers can be made of a ceramic matrix composite, such as a hybrid oxide ceramic matrix composite or an oxide-oxide ceramic matrix composite. The central layer can be made of a material that has high shear strength relative to the inner and outer layers. The ring seal segment according to aspects of the invention can take advantage of the benefits of the different materials so as to better withstand the operational loads of the turbine.
摘要翻译： 本发明的方面涉及可以结合多个材料系统的多层环密封段。 环形密封段可以包括内层，中心层和外层。 内层可以附接到中心层的一侧，并且外层可以附接到中心层的相对侧。 内层和外层可以由陶瓷基复合材料制成，例如杂化氧化物陶瓷基复合材料或氧化物 - 氧化物陶瓷基复合材料。 中心层可以由相对于内层和外层具有高剪切强度的材料制成。 根据本发明的方面的环形密封段可以利用不同材料的优点，以便更好地承受涡轮机的操作负载。
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公开(公告)号：US20080199307A1
公开(公告)日：2008-08-21
申请号：US11707194
申请日：2007-02-15
申请人： Douglas A. Keller
发明人： Douglas A. Keller
CPC分类号： F01D11/006 , F01D5/22 , F16J15/3288 , Y10T29/49297
摘要： A ceramic seal element (200) for use in a turbo-machine comprises a first, rigid portion (210) comprising ceramic fibers (212) bound within a ceramic matrix binder (214), a second, flexible portion (220) comprising ceramic fibers (222), and a third, rigid portion (230) comprising ceramic fibers (232) bound within a ceramic matrix binder (234). Ceramic fibers (222) retain a desired flexibility because they are not bound in ceramic matrix binder. In some embodiments the ceramic fibers (212, 222, 232) are stacked as horizontally disposed layers (225). Also, the fibers (212, 222, 232) of any layer (225) comprise bundles of fibers wherein some of the bundles extend continuously across portions (210, 220, 230). An alternative sealing element (300) comprises a first, rigid portion (310) comprising ceramic fibers (312) that are bound within a ceramic matrix binder (314), and a second, flexible portion (320) that comprises ceramic fibers (313) that retain a desired flexibility. Methods of manufacture are disclosed.
摘要翻译： 用于涡轮机的陶瓷密封元件（200）包括第一刚性部分（210），其包含陶瓷基体粘合剂（214）内的陶瓷纤维（212），第二柔性部分（220），包括陶瓷纤维 （222）和包含陶瓷基体粘合剂（234）中的陶瓷纤维（232）的第三刚性部分（230）。 陶瓷纤维（222）保持所需的柔性，因为它们不结合在陶瓷基体粘合剂中。 在一些实施例中，陶瓷纤维（212,222,232）被堆叠为水平设置的层（225）。 此外，任何层（225）的纤维（212,222,232）都包括纤维束，其中一些束连续延伸穿过部分（210,220,230）。 替代的密封元件（300）包括结合在陶瓷基体粘合剂（314）内的包含陶瓷纤维（312）的第一刚性部分（310）和包含陶瓷纤维（313）的第二柔性部分（320） 保持所需的灵活性。 公开了制造方法。
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公开(公告)号：US20080273967A1
公开(公告)日：2008-11-06
申请号：US11707193
申请日：2007-02-15
IPC分类号： F01D11/12
CPC分类号： F01D11/122 , F05D2230/31 , F05D2230/90 , F05D2240/11 , F05D2240/127 , F05D2250/70 , F05D2250/71 , F05D2250/711 , F05D2260/30 , F05D2300/21
摘要： A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a portion of a gap gas flow path where the inner radial surface may be formed of an abradable ceramic coating and includes a plurality of gas flow protrusions that are oriented transverse to the gap gas flow path. The gas flow protrusions may induce vortices in the gas flow in the gap gas flow path. Additionally, the gas flow protrusions may be series of peaks and depressions between two adjacent peaks, where the depressions have an approximate semicircular shape. The distance between two adjacent peaks may be equal or greater than a width of the depression and the height of a single peak may be six percent or greater than the distance between two adjacent peaks.
摘要翻译： 涡轮发动机环密封件，用于密封涡轮发动机外密封段和涡轮叶片尖端之间的间隙。 涡轮发动机环段可以具有限定间隙气体流动路径的一部分的内部径向表面，其中内部径向表面可以由可磨损陶瓷涂层形成，并且包括多个气体流动突起，其横向于间隙气体 流路。 气流突起可以在间隙气体流动路径中的气流中引起涡流。 此外，气流突起可以是两个相邻峰之间的一系列峰和凹陷，其中凹陷具有近似的半圆形。 两个相邻峰之间的距离可以等于或大于凹陷的宽度，单个峰的高度可以是两个相邻峰之间的距离的6％或更大。
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公开(公告)号：US07371043B2
公开(公告)日：2008-05-13
申请号：US11330597
申请日：2006-01-12
申请人： Douglas A. Keller
发明人： Douglas A. Keller
IPC分类号： F01D11/08
CPC分类号： F01D9/00 , F05D2230/30 , F05D2240/11 , F05D2300/603
摘要： Fabricating a refractory component for a gas turbine engine, such as a turbine shroud ring segment, by arranging refractory fiber tows (24) in a flaired tubular geometry (20) comprising a stem portion (21) and a funnel-shaped portion (22); impregnating the refractory fibers (24) with a ceramic matrix to form a flaired tube (20) of ceramic composite matrix material; at least partially filling the funnel-shaped portion (22) with a ceramic core (30) extending beyond the end of the funnel-shaped portion to provide a working gas containment surface (31); curing the flaired tube (20) and the ceramic core (30) together; cutting the funnel-shaped portion (22) to provide rectangular edges (27); and providing an attachment mechanism (34, 36, 38, 40) on the stem portion (21) for attaching the component to a surrounding support structure. Additional tows (24) may be introduced at intermediate stages to maintain a desired fabric density.
摘要翻译： 通过将耐火纤维丝束（24）布置在包括杆部分（21）和漏斗形部分（22）的带花式管状几何形状（20）中来制造用于燃气涡轮发动机（例如涡轮机护罩环段）的耐火构件， ; 用陶瓷基体浸渍耐火纤维（24）以形成陶瓷复合基质材料的带托管（20）; 至少部分地用延伸超过所述漏斗形部分的端部的陶瓷芯（30）填充所述漏斗形部分（22）以提供工作气体容纳表面（31）; 将所述带托管（20）和所述陶瓷芯（30）一起固化; 切割漏斗形部分（22）以提供矩形边缘（27）; 以及在所述杆部分（21）上设置用于将所述部件附接到周围支撑结构的附接机构（34,36,38,40）。 可以在中间阶段引入额外的丝束（24）以保持所需的织物密度。
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