-
41.发明授权Joining mechanism and method for interlocking modular turbine engine component with a split ring 有权用于将模块化涡轮发动机部件与分离环联动的联接机构和方法公开(公告)号：US08770930B2
公开(公告)日：2014-07-08
申请号：US13023721
申请日：2011-02-09
IPC分类号： F01D9/00
CPC分类号： F01D9/044 , F01D5/147 , F04D29/563 , F04D29/644 , Y02T50/67 , Y02T50/672
摘要： A modular airfoil assembly (200) and related method for interlocking components of an airfoil structure (210) including a platform (220), an airfoil (210) having a shoulder (230) and a stem (232) extending outward from the shoulder. A ring element (100) positioned against the stem (232) secures the shoulder (230) against the platform (210). First and second members (100a, 100b) of the ring element (100) are bonded together with a portion (128j) of a surface (112a) of the second member (100b) extending within and bonded to a portion (128i) of a surface (112b) of the first member (100a).
摘要翻译： 一种用于联锁翼型结构（210）的组件的模块化翼型组件（200）和相关方法，该翼型结构包括平台（220），具有从肩部向外延伸的肩部（230）和杆（232）的翼型件（210）。 定位在杆（232）上的环形元件（100）将肩部（230）固定在平台（210）上。 环形元件（100）的第一和第二构件（100a，100b）与第二构件（100b）的在其内部延伸并结合到其中的部分（128i）的部分（128j） 第一构件（100a）的表面（112b）。
-
公开(公告)号：US20110142684A1
公开(公告)日：2011-06-16
申请号：US12638034
申请日：2009-12-15
CPC分类号： B23P15/04 , F01D5/081 , F01D5/147 , F01D5/3007 , F01D11/008 , F05D2230/51 , F05D2230/52 , F05D2240/40 , F05D2260/36 , Y10T29/49337
摘要： A turbine airfoil (22A) is formed by a first process using a first material. A platform (30A) is formed by a second process using a second material that may be different from the first material. The platform (30A) is assembled around a shank (23A) of the airfoil. One or more pins (36A) extend from the platform into holes (28) in the shank (23A). The platform may be formed in two portions (32A, 34A) and placed around the shank, enclosing it. The two platform portions may be bonded to each other. Alternately, the platform (30B) may be cast around the shank (23B) using a metal alloy with better castability than that of the blade and shank, which may be specialized for thermal tolerance. The pins (36A-36D) or holes for them do not extend to an outer surface (31) of the platform, avoiding stress concentrations.
摘要翻译： 涡轮机翼片（22A）通过使用第一材料的第一工艺形成。 使用可能不同于第一材料的第二材料的第二工艺形成平台（30A）。 平台（30A）组装在机翼的柄（23A）周围。 一个或多个销（36A）从平台延伸到柄（23A）中的孔（28）中。 平台可以形成为两部分（32A，34A）并且围绕柄部放置并包围该平台。 两个平台部分可以彼此结合。 或者，平台（30B）可以使用具有比刀片和柄部更好的铸造性的金属合金围绕杆（23B）铸造，其可以专用于耐热性。 销（36A-36D）或它们的孔不延伸到平台的外表面（31），以避免应力集中。
-
公开(公告)号：US07452182B2
公开(公告)日：2008-11-18
申请号：US11101249
申请日：2005-04-07
申请人： Steven J. Vance , Allister W. James
发明人： Steven J. Vance , Allister W. James
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D5/14 , F01D5/147 , F01D5/28 , F05D2230/50
摘要： Aspects of the invention relate to a modular turbine vane assembly. The vane assembly includes an airfoil portion, an outer shroud and an inner shroud. The airfoil portion can be made of at least two segments. Preferably, the components are connected together so as to permit assembly and disassembly of the vane. Thus, in the event of damage to the vane, repair involves the replacement of only the damaged subcomponents as opposed to the entire vane. The modular design facilitates the use of various materials in the vane, including materials that are dissimilar. Thus, suitable materials can be selected to optimize component life, cooling air usage, aerodynamic performance, and cost. Because the vane is an assemblage of smaller sub-components as opposed to one unitary structure, the individual components of the vane can be more easily manufactured and more intricate features can be included.
摘要翻译： 本发明的方面涉及一种模块化涡轮叶片组件。 叶片组件包括翼型部分，外护罩和内护罩。 翼型部分可以由至少两个部分制成。 优选地，部件连接在一起以允许叶片的组装和拆卸。 因此，在损坏叶片的情况下，修理涉及仅替换损坏的子部件而不是整个叶片。 模块化设计有助于在叶片中使用各种材料，包括不相似的材料。 因此，可以选择合适的材料以优化部件寿命，冷却空气使用，空气动力性能和成本。 因为叶片是与一个单一结构相反的较小子部件的组合，所以叶片的各个部件可以更容易地制造并且可以包括更复杂的特征。
-
公开(公告)号：US08500411B2
公开(公告)日：2013-08-06
申请号：US12794972
申请日：2010-06-07
CPC分类号： B23P15/02 , B22C9/04 , B22C9/10 , F01D5/147 , F01D21/003 , Y10T29/49336
摘要： A turbine airfoil usable in a turbine engine and including a depth indicator for determining outer wall blade thickness. The airfoil may include an outer wall having a plurality of grooves in the outer surface of the outer wall. The grooves may have a depth that represents a desired outer surface and wall thickness of the outer wall. The material forming an outer surface of the outer wall may be removed to be flush with an innermost point in each groove, thereby reducing the wall thickness and increasing efficiency. The plurality of grooves may be positioned in a radially outer region of the airfoil proximate to the tip.
摘要翻译： 一种可用于涡轮发动机并且包括用于确定外壁叶片厚度的深度指示器的涡轮机翼型。 翼型件可以包括在外壁的外表面中具有多个凹槽的外壁。 凹槽可以具有表示外壁的期望外表面和壁厚的深度。 形成外壁的外表面的材料可以被去除以与每个凹槽中的最内点齐平，从而减小壁厚并提高效率。 多个凹槽可以定位在靠近尖端的翼型件的径向外部区域中。
-
公开(公告)号：US08257038B2
公开(公告)日：2012-09-04
申请号：US12024326
申请日：2008-02-01
申请人： Allister W. James
发明人： Allister W. James
IPC分类号： F04D29/34
CPC分类号： F01D5/147 , B22F5/009 , B22F7/08 , B22F2999/00 , F01D9/044 , F05D2230/20 , F05D2230/21 , F05D2240/80 , B22F3/225 , B22F3/1021
摘要： A method of joining a first part together with a second part is disclosed. The method may comprise providing a first part having a first joining portion including a first channel and a second part having a second joining portion including a second channel. The method may further comprise positioning the first part adjacent to the second part such that the first channel and second channel align with one another to define a cavity. The method may still further comprise preparing a mixture comprising at least one of a metal powder and a polymer binder, placing the mixture into the cavity so as to form a preform and solidifying the preform forming a metal element in the cavity. The metal element joins the first part together with the second part.
摘要翻译： 公开了一种将第一部分与第二部分连接的方法。 该方法可以包括提供具有包括第一通道的第一接合部分和具有包括第二通道的第二接合部分的第二部件的第一部件。 该方法还可以包括将第一部分邻近第二部分定位，使得第一通道和第二通道彼此对准以限定空腔。 该方法还可以包括制备包含金属粉末和聚合物粘合剂中的至少一种的混合物，将混合物放入空腔中，以便形成预成型件并固化预成型体，从而在空腔中形成金属元素。 金属元件与第二部分连接在一起。
-
公开(公告)号：US20110299990A1
公开(公告)日：2011-12-08
申请号：US12794972
申请日：2010-06-07
CPC分类号： B23P15/02 , B22C9/04 , B22C9/10 , F01D5/147 , F01D21/003 , Y10T29/49336
摘要： A turbine airfoil usable in a turbine engine and including a depth indicator for determining outer wall blade thickness. The airfoil may include an outer wall having a plurality of grooves in the outer surface of the outer wall. The grooves may have a depth that represents a desired outer surface and wall thickness of the outer wall. The material forming an outer surface of the outer wall may be removed to be flush with an innermost point in each groove, thereby reducing the wall thickness and increasing efficiency. The plurality of grooves may be positioned in a radially outer region of the airfoil proximate to the tip.
摘要翻译： 一种可用于涡轮发动机并且包括用于确定外壁叶片厚度的深度指示器的涡轮机翼型。 翼型件可以包括在外壁的外表面中具有多个凹槽的外壁。 凹槽可以具有表示外壁的期望外表面和壁厚的深度。 形成外壁的外表面的材料可以被去除以与每个凹槽中的最内点齐平，从而减小壁厚并提高效率。 多个槽可以定位在靠近尖端的翼型件的径向外部区域中。
-
公开(公告)号：US20080166585A1
公开(公告)日：2008-07-10
申请号：US11649574
申请日：2007-01-04
申请人： David B. Allen , Allister W. James , David W. Hunt
发明人： David B. Allen , Allister W. James , David W. Hunt
CPC分类号： B23K9/0026 , B23K9/167 , B23K9/23 , B23K9/235 , B23K2103/18 , B23K2103/26 , Y10T428/12493
摘要： A method for welding to a superalloy material without causing cracking of the material. The method includes the steps of depositing a weld strip (18) of a weldable material onto a superalloy substrate material (12) using a spray deposition process (20) and then forming a weldment (26) to the weld strip. None or a controlled amount of the substrate material (12) is melted during the weld in order to maintain the concentration of strengthening elements in the local melt within a zone of weldability. The spray deposition process may be a thermal process such as HVOF or a cold spray process. A groove (16) may be formed in a surface (10) of the superalloy substrate material to receive the weld strip. A diffusion heat treatment step may be used to improve adhesion between the weld strip and the superalloy material.
摘要翻译： 焊接到超合金材料而不引起材料开裂的方法。 该方法包括以下步骤：使用喷雾沉积工艺（20）将焊接材料的焊接条（18）沉积到超合金基底材料（12）上，然后形成焊接条（26）。 在焊接期间没有或受控量的基底材料（12）熔化，以便将局部熔体中的强化元素的浓度保持在可焊性区域内。 喷雾沉积工艺可以是诸如HVOF或冷喷涂工艺的热处理。 可以在超合金基底材料的表面（10）中形成凹槽（16）以接收焊接条。 可以使用扩散热处理步骤来改善焊接条和超合金材料之间的粘附。
-
公开(公告)号：US09726028B2
公开(公告)日：2017-08-08
申请号：US13171699
申请日：2011-06-29
CPC分类号： F01D9/042 , B22D19/0072 , B22D19/04 , F01D11/006 , F05D2300/10 , F05D2300/506 , F05D2300/518 , Y10T29/49323
摘要： A vane assembly (10) having: an airfoil (12) and a shroud (14) held together without metallurgical bonding there between; a channel (22) disposed circumferentially about the airfoil (12), between the airfoil (12) and the shroud (14); and a seal (20) disposed in the channel (22), wherein during operation of a turbine engine having the vane assembly (10) the seal (20) has a sufficient ductility such that a force generated on the seal (20) resulting from relative movement of the airfoil (12) and the shroud (14) is sufficient to plastically deform the seal (20).
-
公开(公告)号：US20130004294A1
公开(公告)日：2013-01-03
申请号：US13171699
申请日：2011-06-29
CPC分类号： F01D9/042 , B22D19/0072 , B22D19/04 , F01D11/006 , F05D2300/10 , F05D2300/506 , F05D2300/518 , Y10T29/49323
摘要： A vane assembly (10) having: an airfoil (12) and a shroud (14) held together without metallurgical bonding there between; a channel (22) disposed circumferentially about the airfoil (12), between the airfoil (12) and the shroud (14); and a seal (20) disposed in the channel (22), wherein during operation of a turbine engine having the vane assembly (10) the seal (20) has a sufficient ductility such that a force generated on the seal (20) resulting from relative movement of the airfoil (12) and the shroud (14) is sufficient to plastically deform the seal (20).
摘要翻译： 一种叶片组件（10），其具有：翼型件（12）和护罩（14），其间保持在一起而不进行冶金结合; 在所述翼型件（12）和所述护罩（14）之间围绕所述翼型件（12）周向设置的通道（22）; 以及设置在通道（22）中的密封件（20），其中在具有叶片组件（10）的涡轮发动机的操作期间，密封件（20）具有足够的延展性，使得在密封件（20）上产生的力由 翼型件（12）和护罩（14）的相对运动足以使密封件（20）塑性变形。
-
50.发明申请HYBRID MANUFACTURING PROCESS AND PRODUCT MADE USING LAMINATED SHEETS AND COMPRESSIVE CASING 有权混合制造工艺和使用层压片和压缩机的产品公开(公告)号：US20120276361A1
公开(公告)日：2012-11-01
申请号：US13094985
申请日：2011-04-27
CPC分类号： B32B3/266 , B28B1/002 , B32B1/00 , B32B2605/00 , B33Y10/00 , Y10T428/249923
摘要： Fabricating a core of a component (34A, 34B, 34C) from a stack (25, 36) of sheets (20) of material with cutouts (22A) in the sheets aligned to form passages (38) in the core. A casing preform (28) is then fitted over the core. The preform is processed to form a casing (29) that brackets at least parts of opposed ends of the stack. Shrinkage of the casing during processing compresses (46) the sheets together. The preform may slide (52) over the core, and may be segmented (28A, 28B, 28C) to fit over the core. A hoop (66) may be fitted and compressed around the segmented casing (29A, 29B, 29C).
摘要翻译： 从片材（20）的堆叠（25,36）制造组件（34A，34B，34C）的芯，其中片材中的切口（22A）被排列成在芯中形成通道（38）。 然后将壳体预制件（28）装配在芯上。 处理预成型件以形成一个壳体（29），该壳体（29）支撑堆叠的相对端的至少部分。 加工过程中外壳的收缩将片材（46）压缩在一起。 预制件可以在芯上滑动（52），并且可以被分段（28A，28B，28C）以配合在芯上。 箍（66）可以围绕分段的壳体（29A，29B，29C）被安装和压缩。
-
-
-
-
-
-
-
-
-
搜索结果
72 条记录 (耗时 0.027 秒)
