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41. 发明授权

US09017027B2 Component having cooling channel with hourglass cross section 有权
标题翻译：具有沙漏横截面的冷却通道的部件
公开(公告)号：US09017027B2
公开(公告)日：2015-04-28
申请号：US13760107
申请日：2013-02-06
申请人： Christian X. Campbell , Ching-Pang Lee
发明人： Christian X. Campbell , Ching-Pang Lee
IPC分类号： F01D5/18 , F01D25/12 , F28F3/04 , F01D5/14 , F28F7/02
CPC分类号： F01D5/183 , F01D5/147 , F01D5/187 , F01D25/12 , F05D2240/304 , F05D2250/13 , F05D2260/2214 , F28F3/048 , F28F7/02
摘要： A cooling channel (36, 36B, 63-66) cools inner surfaces (48, 50) of exterior walls (41, 43) of a component (20, 60). Interior side surfaces (52, 54) of the channel converge to a waist (W2), forming an hourglass shaped transverse profile (46). The inner surfaces (48, 50) may have fins (44) aligned with the coolant flow (22). The fins may have a transverse profile (56A, 56B) highest at mid-width of the inner surfaces (48, 50). Turbulators (92) may be provided on the side surfaces (52, 54) of the channel, and may urge the coolant flow toward the inner surfaces (48, 50). Each turbulator (92) may have a peak (97) that defines the waist of the cooling channel. Each turbulator may have a convex upstream side (93). These elements increase coolant flow in the corners (C) of the channel to more uniformly and efficiently cool the exterior walls (41, 43).
摘要翻译：冷却通道（36,36B，63-66）冷却部件（20,60）的外壁（41,43）的内表面（48,50）。通道的内侧表面（52,54）会聚到腰部（W2），形成沙漏形的横向轮廓（46）。内表面（48,50）可具有与冷却剂流（22）对准的翅片（44）。翅片可以具有在内表面（48,50）的中间宽度处最高的横向轮廓（56A，56B）。紊流器（92）可以设置在通道的侧表面（52,54）上，并且可以促使冷却剂流向内表面（48,50）。每个湍流器（92）可以具有限定冷却通道的腰部的峰（97）。每个湍流器可以具有凸起的上游侧（93）。这些元件增加通道的角部（C）中的冷却剂流动，以更均匀且有效地冷却外壁（41,43）。

42. 发明授权

US09017014B2 Aft outer rim seal arrangement 有权
标题翻译：后外缘密封布置
公开(公告)号：US09017014B2
公开(公告)日：2015-04-28
申请号：US13930482
申请日：2013-06-28
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
IPC分类号： F01D11/08 , F01D25/12 , F01D11/02 , F01D5/18
CPC分类号： F01D11/02 , F01D5/082 , F01D5/18 , F01D5/187 , F01D11/04 , F05D2260/14
摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
摘要翻译：外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面（74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。

43. 发明申请

US20110236221A1 Four-Wall Turbine Airfoil with Thermal Strain Control for Reduced Cycle Fatigue 失效
标题翻译：具有热应变控制以减少循环疲劳的四壁涡轮机翼型
公开(公告)号：US20110236221A1
公开(公告)日：2011-09-29
申请号：US12732386
申请日：2010-03-26
申请人： Christian X. Campbell
发明人： Christian X. Campbell
IPC分类号： F01D5/18
CPC分类号： F01D5/148 , F01D5/187 , F05D2300/50212
摘要： A turbine airfoil (20B) with a thermal expansion control mechanism that increases the airfoil camber (60, 61) under operational heating. The airfoil has four-wall geometry, including pressure side outer and inner walls (26, 28B), and suction side outer and inner walls (32, 34B). It has near-wall cooling channels (31F, 31A, 33F, 33A) between the outer and inner walls. A cooling fluid flow pattern (50C, 50W, 50H) in the airfoil causes the pressure side inner wall (28B) to increase in curvature under operational heating. The pressure side inner wall (28B) is thicker than walls (26, 34B) that oppose it in camber deformation, so it dominates them in collaboration with the suction side outer wall (32), and the airfoil camber increases. This reduces and relocates a maximum stress area (47) from the suction side outer wall (32) to the suction side inner wall (34B, 72) and the pressure side outer wall (26).
摘要翻译：一种具有热膨胀控制机构的涡轮机翼（20B），其在操作加热下增加翼型弧（60,61）。翼型件具有四壁几何形状，包括压力侧外壁和内壁（26,28B）以及吸力侧外壁和内壁（32,34B）。它在外壁和内壁之间具有近壁冷却通道（31F，31A，33F，33A）。机翼中的冷却流体流动图案（50C，50W，50H）使得压力侧内壁（28B）在操作加热下的曲率增加。压力侧内壁（28B）比在外倾变形时与其相反的壁（26,34B）厚，因此它与吸力侧外壁（32）协调地支配它们，并且机翼外倾角增大。这样就将最大应力区域47从吸入侧外壁32吸入吸入侧内壁34B和压力侧外壁26。

44. 发明申请

US20110142639A1 MODULAR TURBINE AIRFOIL AND PLATFORM ASSEMBLY WITH INDEPENDENT ROOT TEETH 失效
标题翻译：模块化涡轮机空气和平台组装，具有独立的根部
公开(公告)号：US20110142639A1
公开(公告)日：2011-06-16
申请号：US12793935
申请日：2010-06-04
申请人： Christian X. Campbell , Daniel O. Davies , Darryl Eng
发明人： Christian X. Campbell , Daniel O. Davies , Darryl Eng
IPC分类号： F01D5/18 , F01D5/00
CPC分类号： F01D5/147 , F01D5/081 , F01D5/3007 , F01D11/008
摘要： A turbine airfoil (22E-H) extends from a shank (23E-H). A platform (30E-H) brackets or surrounds a first portion of the shank (23E-H). Opposed teeth (33, 35) extend laterally from the platform (30E-H) to engage respective slots (50) in a disk. Opposed teeth (25, 27) extend laterally from a second portion of the shank (29) that extends below the platform (30E-H) to engage other slots (52) in the disk. Thus the platform (30E-H) and the shank (23E-H) independently support their own centrifugal loads via their respective teeth. The platform may be formed in two portions (32E-H, 34E-H), that are bonded to each other at matching end-walls (37) and/or via pins (36G) passing through the shank (23E-H). Coolant channels (41, 43) may pass through the shank beside the pins (36G).
摘要翻译：涡轮机翼（22E-H）从柄（23E-H）延伸。平台（30E-H）支架或围绕柄部（23E-H）的第一部分。相对的齿（33,35）从平台（30E-H）横向地延伸以与盘中的相应的槽（50）接合。相对的齿（25,27）从在所述平台（30E-H）下方延伸的所述柄（29）的第二部分横向延伸，以接合所述盘中的其它狭槽（52）。因此，平台（30E-H）和柄（23E-H）通过其相应的齿独立地支撑它们自己的离心载荷。平台可以形成为两个部分（32E-H，34E-H），它们在通过柄（23E-H）的匹配端壁（37）和/或通孔销（36G）处彼此结合。冷却剂通道（41,43）可以穿过销（36G）旁边的柄。

45. 发明申请

US20110110762A1 Damping Element for Reducing the Vibration of an Airfoil 失效
标题翻译：用于减少翼型振动的阻尼元件
公开(公告)号：US20110110762A1
公开(公告)日：2011-05-12
申请号：US12613957
申请日：2009-11-06
申请人： Christian X. Campbell , John J. Marra
发明人： Christian X. Campbell , John J. Marra
IPC分类号： F01D25/04 , F01D5/14 , F01D5/18
CPC分类号： F01D5/16 , F05D2260/20 , F05D2300/21 , F05D2300/603
摘要： An airfoil (10) is provided with a tip (12) having an opening (14) to a center channel (24). A damping element (16) is inserted within the opening of the center channel, to reduce an induced vibration of the airfoil. The mass of the damping element, a spring constant of the damping element within the center channel, and/or a mounting location (58) of the damping element within the center channel may be adjustably varied, to shift a resonance frequency of the airfoil outside a natural operating frequency of the airfoil.
摘要翻译：机翼（10）设置有具有到中心通道（24）的开口（14）的尖端（12）。阻尼元件（16）插入在中心通道的开口内，以减少翼型的感应振动。缓冲元件的质量，中心通道内的阻尼元件的弹簧常数和/或中心通道内的阻尼元件的安装位置（58）可以可调地变化，以使翼型件的共振频率向外移动机翼的自然工作频率。

46. 发明申请

US20110008154A1 Sealing Arrangement for Turbine Engine Having Ceramic Components 有权
标题翻译：具有陶瓷部件的涡轮发动机密封装置
公开(公告)号：US20110008154A1
公开(公告)日：2011-01-13
申请号：US12101412
申请日：2008-04-11
申请人： Christian X. Campbell , Gary B. Merrill
发明人： Christian X. Campbell , Gary B. Merrill
IPC分类号： F01D11/00
CPC分类号： F01D11/006 , F05D2240/11 , F05D2240/80 , F16J15/3288 , F16J15/442 , Y10S416/50
摘要： A sealing arrangement for use in a turbine engine having ceramic components. The sealing arrangement is retained in a seal gap formed between adjacent segments and is compliant to accommodate variations in the size of the seal gap as the adjacent segments move relative to one another.
摘要翻译：一种用于具有陶瓷部件的涡轮发动机中的密封装置。密封装置保持在形成在相邻节段之间的密封间隙中，并且当相邻的片段相对于彼此移动时，其符合容纳密封间隙尺寸的变化。

47. 发明授权

US07726936B2 Turbine engine ring seal 有权
标题翻译：涡轮发动机环密封
公开(公告)号：US07726936B2
公开(公告)日：2010-06-01
申请号：US11492590
申请日：2006-07-25
申请人： Douglas A. Keller , Steven J. Vance , Christian X. Campbell
发明人： Douglas A. Keller , Steven J. Vance , Christian X. Campbell
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。

48. 发明申请

US20100032875A1 Processing method for solid core ceramic matrix composite airfoil 有权
标题翻译：固体陶瓷基体复合翼型加工方法
公开(公告)号：US20100032875A1
公开(公告)日：2010-02-11
申请号：US11082415
申请日：2005-03-17
申请人： Gary B. Merrill , Christian X. Campbell , Thomas Barrett Jackson
发明人： Gary B. Merrill , Christian X. Campbell , Thomas Barrett Jackson
IPC分类号： B28B1/00 , C04B35/00 , B32B3/00
CPC分类号： B28B1/008 , B28B19/00 , B32B1/00 , B32B1/08 , B32B3/04 , B32B9/005 , B32B2264/101 , B32B2264/102 , C04B35/50 , C04B35/80 , C04B38/067 , C04B2235/3229 , Y10T428/24479
摘要： A method of processing solid core ceramic matrix composite articles. The method improves the physical characteristics of the article by forming the airfoil using a co-processing method wherein a refractory ceramic is cast against a preformed ceramic matrix composite (CMC) shell. In one aspect, the shell is continuous to help prevent delaminations. In another aspect, the shell is open. In one embodiment, the article includes a split line. The split line helps the article to be less susceptible to damage caused from internal strain.
摘要翻译：固体陶瓷基复合材料的加工方法。该方法通过使用协同处理方法形成翼型来改善制品的物理特性，其中耐火陶瓷与预成型的陶瓷基复合材料（CMC）壳体相对铸造。在一个方面，壳是连续的以帮助防止分层。另一方面，壳体是敞开的。在一个实施例中，物品包括分割线。分割线帮助物品不易受内部应变造成的损坏。

49. 发明授权

US08684692B2 Cooled snubber structure for turbine blades 失效
标题翻译：涡轮叶片的冷却缓冲结构
公开(公告)号：US08684692B2
公开(公告)日：2014-04-01
申请号：US13023651
申请日：2011-02-09
申请人： Clinton A. Mayer , Christian X. Campbell , Andrew Whalley , John J. Marra
发明人： Clinton A. Mayer , Christian X. Campbell , Andrew Whalley , John J. Marra
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D5/187 , F01D5/22 , F05D2260/221
摘要： A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade.
摘要翻译：涡轮发动机中的涡轮叶片组件。涡轮叶片组件包括涡轮叶片和第一缓冲结构。涡轮机叶片包括内部冷却通道，其包含冷却空气。第一缓冲结构从涡轮机叶片的侧壁向外延伸并且包括从涡轮叶片的内部冷却通道接收冷却空气的中空内部部分。

50. 发明授权

US08535004B2 Four-wall turbine airfoil with thermal strain control for reduced cycle fatigue 失效
标题翻译：具有热应变控制的四壁涡轮机翼型，可减少循环疲劳
公开(公告)号：US08535004B2
公开(公告)日：2013-09-17
申请号：US12732386
申请日：2010-03-26
申请人： Christian X. Campbell
发明人： Christian X. Campbell
IPC分类号： F01D5/08 , F01D5/18
CPC分类号： F01D5/148 , F01D5/187 , F05D2300/50212
摘要： A turbine airfoil (20B) with a thermal expansion control mechanism that increases the airfoil camber (60, 61) under operational heating. The airfoil has four-wall geometry, including pressure side outer and inner walls (26, 28B), and suction side outer and inner walls (32, 34B). It has near-wall cooling channels (31F, 31A, 33F, 33A) between the outer and inner walls. A cooling fluid flow pattern (50C, 50W, 50H) in the airfoil causes the pressure side inner wall (28B) to increase in curvature under operational heating. The pressure side inner wall (28B) is thicker than walls (26, 34B) that oppose it in camber deformation, so it dominates them in collaboration with the suction side outer wall (32), and the airfoil camber increases. This reduces and relocates a maximum stress area (47) from the suction side outer wall (32) to the suction side inner wall (34B, 72) and the pressure side outer wall (26).
摘要翻译：一种具有热膨胀控制机构的涡轮机翼（20B），其在操作加热下增加翼型弧（60,61）。翼型件具有四壁几何形状，包括压力侧外壁和内壁（26,28B）以及吸力侧外壁和内壁（32,34B）。它在外壁和内壁之间具有近壁冷却通道（31F，31A，33F，33A）。翼型件中的冷却流体流动模式（50C，50W，50H）使得压力侧内壁（28B）在操作加热下的曲率增加。压力侧内壁（28B）比在外倾变形时与其相反的壁（26,34B）更厚，因此它与吸力侧外壁（32）协调地支配它们，并且机翼外倾角增大。这样就将最大应力区域47从吸入侧外壁32吸入吸入侧内壁34B和压力侧外壁26。

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