-
公开(公告)号：US07258530B2
公开(公告)日：2007-08-21
申请号：US11040464
申请日：2005-01-21
IPC分类号： F01D5/14
CPC分类号： F01D5/284 , F01D5/147 , F01D5/282 , Y10T29/49337 , Y10T29/49339
摘要： An airfoil (44) formed of a plurality of pre-fired structural CMC panels (46, 48, 50, 52). Each panel is formed to have an open shape having opposed ends (54) that are free to move during the drying, curing and/or firing of the CMC material in order to minimize interlaminar stresses caused by anisotropic sintering shrinkage. The panels are at least partially pre-shrunk prior to being joined together to form the desired structure, such as an airfoil (42) for a gas turbine engine. The panels may be joined together using a backing member (30), using flanged ends (54) and a clamp (56), and/or with a bond material (36), for example.
摘要翻译： 由多个预烧结构的CMC板（46,48,50,52）形成的翼型件（44）。 每个板形成为具有相对端（54）的开放形状，其在CMC材料的干燥，固化和/或烧制期间自由移动，以便最小化由各向异性烧结收缩引起的层间应力。 在连接在一起以形成期望的结构之前，板至少部分地预收缩，例如用于燃气涡轮发动机的翼型件（42）。 例如，使用凸缘端部（54）和夹具（56）和/或与粘合材料（36）一起使用背衬构件（30）将面板连接在一起。
-
公开(公告)号：US07255535B2
公开(公告)日：2007-08-14
申请号：US11002030
申请日：2004-12-02
CPC分类号： F01D5/147 , F01D5/187 , F01D5/284 , F05D2260/201 , F05D2300/501 , F05D2300/603 , F05D2300/702
摘要： Embodiments of the invention relate to various cooling systems for a turbine vane made of stacked ceramic matrix composite (CMC) laminates. Each airfoil-shaped laminate has an in-plane direction and a through thickness direction substantially normal to the in-plane direction. The laminates have anisotropic strength characteristics in which the in-plane tensile strength is substantially greater than the through thickness tensile strength. Such a vane construction lends itself to the inclusion of various cooling features in individual laminates using conventional manufacturing and forming techniques. When assembled in a radial stack, the cooling features in the individual laminates can cooperate to form intricate three dimensional cooling systems in the vane.
摘要翻译： 本发明的实施例涉及由堆叠的陶瓷基质复合（CMC）层压体制成的涡轮叶片的各种冷却系统。 每个翼型层压板具有基本上垂直于面内方向的面内方向和贯穿厚度方向。 层压板具有各向异性强度特性，其中面内拉伸强度基本上大于贯穿厚度拉伸强度。 这种叶片结构使得能够使用常规的制造和成形技术将各种冷却特征包含在单独的层压板中。 当组装成径向堆叠时，单个层压板中的冷却特征可以协作以在叶片中形成复杂的三维冷却系统。
-
公开(公告)号：US07351364B2
公开(公告)日：2008-04-01
申请号：US10767012
申请日：2004-01-29
CPC分类号： B28B7/342 , B28B11/08 , B28B19/00 , C04B2235/6028 , F05D2300/6033 , Y10S264/44
摘要： A method of manufacturing a hybrid structure (100) having a layer of CMC material (28) defining an interior passageway (24) and a layer of ceramic insulating material (18) lining the passageway. The method includes the step of casting the insulating material to a first thickness required for effective casting but in excess of a desired second thickness for use of the hybrid structure. An inner mold (14) defining a net shape desired for the passageway remains in place after the casting step to mechanically support the insulating material during a machining process used to reduce the thickness of the insulating material from the as-cast first thickness to the desired second thickness. The inner mold also provides support as the CMC material is deposited onto the insulating material. The inner mold may include a fugitive material portion (20) to facilitate its removal after the CMC material is formed.
摘要翻译： 一种制造具有限定内部通道（24）的CMC材料层（28）和衬套通道的陶瓷绝缘材料层（18）的混合结构（100）的方法。 该方法包括将绝缘材料浇铸到有效铸造所需的第一厚度但超过所需的第二厚度以用于混合结构的步骤。 限定通道所需的净形状的内模（14）在铸造步骤之后保持就位，以在用于将绝缘材料的厚度从铸造第一厚度减小到期望的机械加工过程期间机械地支撑绝缘材料 第二厚度。 当CMC材料沉积到绝缘材料上时，内模还提供支撑。 内部模具可以包括短暂材料部分（20），以便在形成CMC材料之后便于其移除。
-
公开(公告)号：US08528339B2
公开(公告)日：2013-09-10
申请号：US11784154
申请日：2007-04-05
IPC分类号： F04D29/54
CPC分类号： F01D5/147 , F01D5/282 , F05D2300/603
摘要： A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material.
摘要翻译： 提供了可用作一种或多种金属部件的替代物的用于涡轮发动机的堆叠层叠部件。 堆叠的层叠部件可以具有通过堆叠和层压层以形成沿着热气体路径的径向内表面的过程形成的主体。 这些层可以基本上垂直于径向内表面。 这些层可以是至少第一材料的第一层和第二材料的第二层。 至少第一种材料是陶瓷基复合材料。 第二材料可以具有比第一材料更高的导热性或更高的蠕变强度。
-
公开(公告)号：US07153096B2
公开(公告)日：2006-12-26
申请号：US11002028
申请日：2004-12-02
IPC分类号： F01D9/00
CPC分类号： F04D29/388 , F01D5/147 , F05D2230/23 , F05D2300/601 , F05D2300/603 , F05D2300/614 , Y10T428/249928 , Y10T428/249929
摘要： Embodiments of the invention relate to a robust turbine vane made of stacked airfoil-shaped CMC laminates. Each laminate has an in-plane direction and a through thickness direction substantially normal to the in-plane direction. The laminates have anisotropic strength characteristics in which the in-plane tensile strength is substantially greater than the through thickness tensile strength. Thus, the laminates can provide strength in the direction of high thermal gradients and, thus, withstand the associated high thermal stresses. The laminates are relatively weak in through thickness (interlaminar) tension, but, in operation, relatively low through thickness tensile stresses can be expected. The laminates can be strong in through thickness compression; accordingly, the laminate stack can be held in through thickness compression by one or more fasteners. The CMC material can permit the inclusion of additional features such as cooling passages, ribs, spars, and thermal coatings, without compromising the strength characteristics of the material.
摘要翻译： 本发明的实施例涉及一种由层叠翼型CMC层压板制成的坚固的涡轮叶片。 每个层压板具有基本上垂直于面内方向的面内方向和贯穿厚度方向。 层压板具有各向异性强度特性，其中面内拉伸强度基本上大于贯穿厚度拉伸强度。 因此，层压板可以在高热梯度的方向上提供强度，并因此承受相关联的高热应力。 层压板在贯穿厚度（层间）张力方面相对较弱，但是在操作中可以预期相对低的贯穿厚度的拉伸应力。 层压板可以通过厚度压缩强; 因此，可以通过一个或多个紧固件将叠层叠层保持在通过厚度压缩中。 CMC材料可以允许包括额外的特征，例如冷却通道，肋，翼梁和热涂层，而不损害材料的强度特性。
-
6.发明申请Ceramic matrix composite surfaces with open features for improved bonding to coatings 审中-公开具有开放特征的陶瓷基体复合材料表面，用于改善与涂层的结合公开(公告)号：US20100119777A1
公开(公告)日：2010-05-13
申请号：US11600709
申请日：2006-11-16
CPC分类号： C04B41/5027 , B32B5/12 , B32B5/26 , B32B5/30 , B32B2260/025 , B32B2264/107 , B32B2307/304 , C04B41/009 , C04B41/87 , D03D15/0016 , D03D15/02 , D03D25/005 , D04C1/06 , D10B2505/02 , F05C2253/02 , F05C2253/04 , F05C2253/12 , Y10T428/24479 , C04B20/004 , C04B35/80
摘要： A method to form an improved hybrid ceramic matrix composite structure comprises providing a ceramic matrix composite (CMC) with open features at a surface and applying a thermal barrier coating to the surface. The thermal barrier coating is preferably a friable graded insulation coating (FGI) having hollow ceramic spheres. For acceptance of a FGI coating the open features have a center-to-center separation distance in one or more directions that is between about 100 and about 1,000 percent of the diameter of the hollow ceramic spheres in the FGI and a depth that is between about 20 percent and about 200 percent of the diameter of the hollow ceramic spheres in the FGI. The open feature can result from the winding of tows about a mandrel; the lay-up of fabric including a surface fabric having an open weave; or the use of a 3-D weave, or a 3-D braid.
摘要翻译： 形成改进的混合陶瓷基质复合结构的方法包括提供在表面上具有开放特征的陶瓷基质复合材料（CMC），并向表面施加热障涂层。 隔热涂层优选是具有中空陶瓷球的易碎梯度绝缘涂层（FGI）。 为了接受FGI涂层，开口特征在一个或多个方向上具有中心到中心的间隔距离，其在FGI中的中空陶瓷球的直径的大约100％到大约1000％之间，并且在大约 在FGI中的中空陶瓷球的直径的20％和约200％。 打开的特征可以由围绕心轴缠绕的丝束产生; 包括具有开放编织物的表面织物的织物铺设; 或使用3-D编织物或3-D编织物。
-
公开(公告)号：US07311790B2
公开(公告)日：2007-12-25
申请号：US10767013
申请日：2004-01-29
CPC分类号： B28B19/0053 , B28B21/42 , F05D2300/6033 , F23R3/007
摘要： A hybrid structure (50) and method of manufacturing the same including a structural ceramic matrix composite (CMC) material (42) coated with a layer of ceramic insulating tiles (24). Individual ceramic tiles are attached to a surface (22) of a mold (20). The exterior surface (32) of the tiles may be subjected to a mechanical process such as machining with the mold in place to provide mechanical support for the tiles. A layer of CMC material is then applied to bond the tiles and the CMC material together into a hybrid structure. The mold may include a fugitive material portion (26) to facilitate removal of the mold when the hybrid structure has a complex shape. Tiles located in different regions of the structure may have different compositions and/or dimensions. The gaps between adjacent tiles may be filled from the outside before the CMC material is applied or from the inside after the mold is removed.
摘要翻译： 一种混合结构（50）及其制造方法，包括涂覆有陶瓷绝缘砖（24）层的结构陶瓷基复合材料（CMC）材料（42）。 单个陶瓷砖附接到模具（20）的表面（22）。 瓦片的外表面（32）可以经受机械加工，例如用模具进行机械加工，以为瓦片提供机械支撑。 然后施加一层CMC材料以将瓷砖和CMC材料结合在一起成为混合结构。 当混合结构具有复杂的形状时，模具可以包括短片材料部分（26），以便于去除模具。 位于结构的不同区域的瓷砖可以具有不同的组成和/或尺寸。 相邻瓦片之间的间隙可以在CMC材料施加之前从外部填充，或者在模具移除之后从内部填充。
-
公开(公告)号：US20100251721A1
公开(公告)日：2010-10-07
申请号：US11784154
申请日：2007-04-05
CPC分类号： F01D5/147 , F01D5/282 , F05D2300/603
摘要： A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material.
摘要翻译： 提供了可用作一种或多种金属部件的替代物的用于涡轮发动机的堆叠层叠部件。 堆叠的层叠部件可以具有通过堆叠和层压层以形成沿着热气体路径的径向内表面的过程形成的主体。 这些层可以基本上垂直于径向内表面。 这些层可以是至少第一材料的第一层和第二材料的第二层。 至少第一种材料是陶瓷基复合材料。 第二材料可以具有比第一材料更高的导热性或更高的蠕变强度。
-
公开(公告)号：US07247003B2
公开(公告)日：2007-07-24
申请号：US11031797
申请日：2005-01-07
申请人： Michael A. Burke , Jay A. Morrison , Steven James Vance , Daniel G. Thompson , Vijay Parthasarathy , Gary B. Merrill , Douglas Allen Keller
发明人： Michael A. Burke , Jay A. Morrison , Steven James Vance , Daniel G. Thompson , Vijay Parthasarathy , Gary B. Merrill , Douglas Allen Keller
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/284 , F04D29/388 , F05D2230/23 , F05D2300/601 , F05D2300/603 , F05D2300/614
摘要： A stacked ceramic matrix composite lamellate assembly (10) including shear force bearing structures (48) for resisting relative sliding movement between adjacent lamellae. The shear force bearing structures may take the form of a cross-lamellar stitch (50), a shear pin (62), a warp (90) in the lamellae, a tongue (104) and groove (98) structure, or an inter-lamellar sealing member (112), in various embodiments. Each shear force bearing structure secures a subset of the lamellae, with at least one lamella being common between adjacent subsets in order to secure the entire assembly.
摘要翻译： 一种层叠的陶瓷基复合材料层状组件（10），其包括用于抵抗相邻薄片之间的相对滑动运动的剪切力轴承结构（48）。 剪切力承载结构可以采取跨层状缝合（50），剪切销（62），薄片中的经线（90），舌状物（104）和凹槽（98）结构的形式， - 绝缘密封件（112）。 每个剪切力轴承结构确保薄片的一个子集，其中至少一个薄片在相邻子集之间是共同的，以便固定整个组件。
-
公开(公告)号：US08313794B2
公开(公告)日：2012-11-20
申请号：US12006700
申请日：2008-01-04
申请人： Steven James Vance
发明人： Steven James Vance
CPC分类号： C04B41/009 , C04B41/5092 , C04B41/85 , C23C4/12 , F01D5/288 , F05D2230/90 , F05D2300/611 , Y10T29/4932 , Y10T29/49737 , Y10T29/49742 , Y10T29/49982 , Y10T428/31504 , C04B14/02 , C04B14/301 , C04B2103/54 , C04B35/80
摘要： Thermally insulating layer incorporating a distinguishing agent and method for inspecting the insulating layer are provided. The distinguishing agent may be used for determining a remaining thickness of the thermally insulating layer.
摘要翻译： 提供了包含鉴别剂的绝热层和用于检查绝缘层的方法。 鉴别剂可以用于确定绝热层的剩余厚度。
-
-
-
-
-
-
-
-
-
搜索结果
13 条记录 (耗时 0.023 秒)
