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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：US20090071160A1
公开(公告)日：2009-03-19
申请号：US11855623
申请日：2007-09-14
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：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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14.发明授权Apparatus comprising a CMC-comprising body and compliant porous element preloaded within an outer metal shell 有权装置包括预先装载在外部金属壳内的包含CMC的主体和柔性多孔元件公开(公告)号：US09127565B2
公开(公告)日：2015-09-08
申请号：US12104049
申请日：2008-04-16
CPC分类号： F01D25/005 , F01D9/023 , F05D2300/21 , F23M5/00 , F23M2900/05004 , F23R3/002 , F23R2900/00017 , F23R2900/03041 , F23R2900/03042
摘要： An apparatus includes a metal shell (200, 300) surrounding a body (230, 330) that is made of a ceramic matrix composite (CMC) material (231) The metal shell defines a space (250) adapted to contain the body and includes at least one protrusion (220) adapted to contact the body. A compliant porous element (240) is adapted to fit in the space between the metal shell and the body. A preload spring (260, 360) is provided in an urging orientation with the body wherein the preload spring is positioned against a first region (333) of the body and is adapted to urge the body toward one of the protrusions positioned against a second region (335) generally opposite the first region, and also to preload the compliant porous element. One of the protrusions may be a hard stop, and in the preload, one of the protrusions may be loaded.
摘要翻译： 一种装置包括围绕由陶瓷基体复合材料（CMC）材料（231）制成的主体（230,330）的金属壳（200,300）。金属壳限定适于容纳主体的空间（250），并且包括 至少一个适于接触身体的突起（220）。 柔性多孔元件（240）适于装配在金属壳体与主体之间的空间中。 预压弹簧（260,360）以与所述主体相关的推动方向设置，其中所述预载弹簧抵靠所述主体的第一区域（333）定位，并且适于将所述主体推向所述突起中的一个，所述突起定位成抵靠第二区域 （335）通常与第一区域相对，并且还用于预加载柔性多孔元件。 突起中的一个可以是硬停止，并且在预载中，可以加载一个突起。
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公开(公告)号：US08167573B2
公开(公告)日：2012-05-01
申请号：US12233878
申请日：2008-09-19
申请人： Gary B. Merrill , Douglas A. Keller
发明人： Gary B. Merrill , Douglas A. Keller
CPC分类号： F01D5/288 , F05C2253/24 , F05D2230/236 , F05D2230/40 , F05D2300/21 , F05D2300/603 , F05D2300/702
摘要： A gas turbine airfoil (20) having a load-bearing core (30). A honeycomb structure (40A, 42A) is attached to pressure and/or suction sides (22, 24) of the core and is filled with ceramic insulation (50). A ceramic matrix composite boot (60A, 60B, 60C) may cover the leading edge (26) of the core. Edges (61, 62) of the boot may be attached to the core by rows of pins (63A, 63B) or by flanges (65) inserted in slots (69) in the core. The pins may be formed in place by forming pin holes (64) in the boot, clamping the boot onto the core, filling the pin holes with metal or ceramic and metal particles, and heating the particles for internal cohesion and solid-state diffusion bonding (66) with the core. The boot may have a central portion (71) that is not bonded to the core to allow differential thermal expansion.
摘要翻译： 一种具有承载芯（30）的燃气轮机翼型件（20）。 蜂窝结构体（40A，42A）被安装在芯的压力和/或吸力侧（22,24）上，并且填充有陶瓷绝缘体（50）。 陶瓷基复合护罩（60A，60B，60C）可以覆盖芯的前缘（26）。 靴子的边缘（61,62）可以通过一排销（63A，63B）或通过插入到芯中的槽（69）中的法兰（65）附接到芯。 销可以通过在靴子中形成销孔（64）而形成在适当的位置，将靴子夹紧到芯上，用金属或陶瓷和金属颗粒填充针孔，并加热颗粒以进行内部内聚和固态扩散粘合 （66）与核心。 靴子可以具有不结合到芯部以允许差异热膨胀的中心部分（71）。
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公开(公告)号：US07393183B2
公开(公告)日：2008-07-01
申请号：US11156196
申请日：2005-06-17
申请人： Douglas A. Keller
发明人： Douglas A. Keller
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/189 , F01D5/282 , F01D5/284 , F05D2230/60 , F05D2230/64 , F05D2240/122 , F05D2240/30 , F05D2240/304 , F05D2300/21 , F05D2300/603
摘要： A trailing edge attachment for a composite turbine airfoil. The trailing edge attachment may include an attachment device for attaching the trailing edge attachment to the airfoil. The attachment device may include a plurality of pins extending through the attachment device and into the trailing edge blade. The trailing edge attachment may also include a spanwise cooling channel for feeding a plurality of cooling channels extending between a leading edge of the trailing edge attachment and a trailing edge of the attachment device. The attachment device may be configured to place the leading edge of the composite airfoil in compression, thereby increasing the strength of the composite airfoil.
摘要翻译： 用于复合涡轮机翼型的后缘附件。 后缘附件可以包括用于将后缘附件附接到翼型件的附接装置。 附接装置可以包括延伸穿过附接装置并进入后缘叶片的多个销。 后缘附件还可以包括翼展式冷却通道，用于供给在后缘附件的前缘和附接装置的后缘之间延伸的多个冷却通道。 附接装置可以构造成将复合翼型件的前缘放置在压缩状态，从而增加复合翼型件的强度。
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公开(公告)号：US20100104426A1
公开(公告)日：2010-04-29
申请号：US11492590
申请日：2006-07-25
IPC分类号： F02C7/28
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：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：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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