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31. 发明申请

US20150003973A1 AFT OUTER RIM SEAL ARRANGEMENT 有权
标题翻译： AFT外部RIM密封安排
公开(公告)号：US20150003973A1
公开(公告)日：2015-01-01
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： F01D11/02 , 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。

32. 发明授权

US08720526B1 Process for forming a long gas turbine engine blade having a main wall with a thin portion near a tip 有权
标题翻译：用于形成具有在尖端附近具有薄壁部分的主壁的长燃气涡轮发动机叶片的方法
公开(公告)号：US08720526B1
公开(公告)日：2014-05-13
申请号：US13675345
申请日：2012-11-13
申请人： Christian X. Campbell , Dimitrios Thomaidis
发明人： Christian X. Campbell , Dimitrios Thomaidis
IPC分类号： B22D46/00
CPC分类号： B22D46/00 , F01D5/147 , F01D5/187 , F05D2230/10 , F05D2230/21
摘要： A process is provided for forming an airfoil for a gas turbine engine involving: forming a casting of a gas turbine engine airfoil having a main wall and an interior cavity, the main wall having a wall thickness extending from an external surface of the outer wall to the interior cavity, an outer section of the main wall extending from a location between a base and a tip of the airfoil casting to the tip having a wall thickness greater than a final thickness. The process may further involve effecting movement, using a computer system, of a material removal apparatus and the casting relative to one another such that a layer of material is removed from the casting at one or more radial portions along the main wall of the casting.
摘要翻译：提供了一种用于形成用于燃气涡轮发动机的翼型件的方法，包括：形成具有主壁和内腔的燃气涡轮发动机翼型的铸件，所述主壁具有从外壁的外表面延伸到壁厚所述内部空腔，所述主壁的外部部分从所述翼型铸件的基部和尖端之间的位置延伸到具有大于最终厚度的壁厚的尖端。该方法可以进一步包括使用计算机系统实现材料去除装置和相对于彼此的铸造的移动，使得沿着铸件的主壁的一个或多个径向部分从铸件移除材料层。

33. 发明授权

US08579593B2 Damping element for reducing the vibration of an airfoil 失效
标题翻译：用于减小翼型振动的阻尼元件
公开(公告)号：US08579593B2
公开(公告)日：2013-11-12
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： F01D5/14 , F01D5/16 , 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。

34. 发明授权

US07837438B2 Vane assembly with metal trailing edge segment 有权
标题翻译：具有金属后缘段的叶片组件
公开(公告)号：US07837438B2
公开(公告)日：2010-11-23
申请号：US11901551
申请日：2007-09-18
申请人： Christian X. Campbell
发明人： Christian X. Campbell
IPC分类号： F01D1/02
CPC分类号： F01D5/147 , F01D5/146 , F05D2240/301 , F05D2240/57 , F05D2260/20 , F05D2260/221 , F05D2300/21 , F05D2300/603
摘要： Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. The forward and aft segments cannot be directly joined to each other because of differences in their rates of thermal expansion and contraction. The forward and aft segments can be positioned substantially proximate to each other so as to form a gap therebetween. In one embodiment, the gap can be substantially sealed by providing a coupling insert or leaf springs in the gap. A separate metal aft segment can take advantage of the beneficial thermal properties of the metal to improve cooling efficiency at the trailing edge without limiting the rest of the vane to being made out of metal.
摘要翻译：本发明的实施例涉及由前部翼型段和后部翼型段形成的叶片组件。后段由金属制成并且可以限定叶片组件的后缘。前段可由陶瓷，CMC或金属制成。由于其热膨胀和收缩率的差异，前部和后部部分不能彼此直接连接。前段和后段可以基本上彼此靠近地定位，以便在它们之间形成间隙。在一个实施例中，通过在间隙中设置联接插件或板簧可以实现密封。单独的金属后部段可以利用金属的有益的热性质来提高后缘处的冷却效率，而不会限制叶片的其余部分被制成金属。

35. 发明申请

US20100104426A1 TURBINE ENGINE RING SEAL 有权
标题翻译：涡轮发动机密封圈
公开(公告)号：US20100104426A1
公开(公告)日：2010-04-29
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： 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。

36. 发明申请

US20100056006A1 MULTILAYERED CERAMIC MATRIX COMPOSITE STRUCTURE HAVING INCREASED STRUCTURAL STRENGTH 有权
标题翻译：具有增加结构强度的多层陶瓷基体复合结构
公开(公告)号：US20100056006A1
公开(公告)日：2010-03-04
申请号：US12204092
申请日：2008-09-04
申请人： Christian X. Campbell
发明人： Christian X. Campbell
IPC分类号： D03D11/00 , B29C65/70
CPC分类号： D03D11/00 , D03D15/0016 , D03D25/005 , D10B2505/02 , Y10T442/3195 , Y10T442/3472 , Y10T442/3528 , Y10T442/3602
摘要： A multilayer ceramic matrix composite structure is disclosed. The ceramic matrix composite structure may include a three-dimensional weave fabric forming a core layer. The ceramic matrix composite structure may also include a two-dimensional weave fabric attached to an outer top surface of the three-dimensional weave fabric such that the two-dimensional weave fabric forms a top layer, and a two-dimensional weave fabric attached to an outer bottom surface of the three-dimensional weave fabric generally opposite to the outer top surface such that the two-dimensional weave fabric forms a bottom layer. The structure may include increased interlaminar shear strength.
摘要翻译：公开了一种多层陶瓷基复合结构。陶瓷基复合结构可以包括形成芯层的三维织造织物。陶瓷基体复合结构还可以包括连接到三维编织织物的外顶表面上的二维编织织物，使得二维编织织物形成顶层，和二维编织织物附着于通常与外顶表面相对的三维编织织物的外底表面，使得二维编织织物形成底层。该结构可以包括增加的层间剪切强度。

37. 发明授权

US07563071B2 Pin-loaded mounting apparatus for a refractory component in a combustion turbine engine 失效
$Pin-loaded mounting apparatus for a refractory component in a combustion turbine engine$
标题翻译：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
申请人： Christian X. Campbell , Douglas A. Keller , Malberto F. Gonzalez
发明人： Christian X. Campbell , Douglas A. Keller , Malberto F. Gonzalez
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。

38. 发明申请

US20090003988A1 Vane assembly with metal trailing edge segment 有权
标题翻译：具有金属后缘段的叶片组件
公开(公告)号：US20090003988A1
公开(公告)日：2009-01-01
申请号：US11901551
申请日：2007-09-18
申请人： Christian X. Campbell
发明人： Christian X. Campbell
IPC分类号： F04D29/54 , F04D29/58
CPC分类号： F01D5/147 , F01D5/146 , F05D2240/301 , F05D2240/57 , F05D2260/20 , F05D2260/221 , F05D2300/21 , F05D2300/603
摘要： Embodiments of the invention relate to a vane assembly formed by a forward airfoil segment and an aft airfoil segment. The aft segment is made of metal and can define the trailing edge of the vane assembly. The forward segment can be made of ceramic, CMC or metal. The forward and aft segments cannot be directly joined to each other because of differences in their rates of thermal expansion and contraction. The forward and aft segments can be positioned substantially proximate to each other so as to form a gap therebetween. In one embodiment, the gap can be substantially sealed by providing a coupling insert or leaf springs in the gap. A separate metal aft segment can take advantage of the beneficial thermal properties of the metal to improve cooling efficiency at the trailing edge without limiting the rest of the vane to being made out of metal.
摘要翻译：本发明的实施例涉及由前部翼型段和后部翼型段形成的叶片组件。后段由金属制成并且可以限定叶片组件的后缘。前段可由陶瓷，CMC或金属制成。由于其热膨胀和收缩率的差异，前部和后部部分不能彼此直接连接。前段和后段可以基本上彼此靠近地定位，以便在它们之间形成间隙。在一个实施例中，通过在间隙中设置联接插件或板簧可以实现密封。单独的金属后部段可以利用金属的有益的热性质来提高后缘处的冷却效率，而不会限制叶片的其余部分被制成金属。

39. 发明授权

US06528190B1 Fiber coating compounds for reinforced ceramic matrix composites 有权
标题翻译：用于增强陶瓷基复合材料的纤维涂层化合物
公开(公告)号：US06528190B1
公开(公告)日：2003-03-04
申请号：US09631097
申请日：2000-08-02
申请人： Christian X. Campbell , Jay E. Lane
发明人： Christian X. Campbell , Jay E. Lane
IPC分类号： B32B900
CPC分类号： C04B35/62847 , C04B35/117 , C04B35/185 , C04B35/44 , C04B35/803 , C04B2235/3225 , C04B2235/5224 , C04B2235/5264 , C04B2235/764 , C04B2235/77 , F23R3/007 , Y10T428/249928 , Y10T428/24993 , Y10T428/26
摘要： A composite (20) has a matrix (10), preferably of ceramic, interspersed with reinforcement structures (12), preferably ceramic fibers, coated with a material (14) selected from ZrGeO4, HfGeO4 and CeGeO4, where the composite can be used as a component in high temperature turbines.
摘要翻译：复合材料（20）具有优选陶瓷的基体（10），散布有加强结构（12），优选陶瓷纤维，涂覆有选自ZrGeO4，HfGeO4和CeGeO4的材料（14），其中复合材料可以用作高温涡轮机组件。

40. 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）。

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