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21. 发明申请

US20090324841A1 METHOD OF RESTORING NEAR-WALL COOLED TURBINE COMPONENTS 审中-公开
标题翻译：恢复近壁冷却涡轮机组件的方法
公开(公告)号：US20090324841A1
公开(公告)日：2009-12-31
申请号：US12117954
申请日：2008-05-09
申请人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
发明人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
IPC分类号： B32B43/00 , B05D1/08
CPC分类号： C23C28/3455 , C23C4/01 , C23C4/02 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345
摘要： A method is provided for restoring a near-wall channeled gas turbine engine component (100, 200) which has been exposed to engine operation. In a representative embodiment, a cooling channel (102) of the component (100) is filled with a polymer that solidifies to form a preform material (110) in the cooling channel (102). Then existing outer wall layers (106, 108) of the component (100) are removed, thereby exposing in part the preform material (110). New outer wall layers (106-N, 108-N) are applied over the component (100), and this may be done while a cooling flow is also applied to the component (100). Then the preform material (110) is removed without destroying the new outer wall layers (106-N, 108-N). The new outer wall layers (106-N, 108-N) may be applied by HVOF processes or by other methods.
摘要翻译：提供了一种用于恢复暴露于发动机操作的近壁通道燃气涡轮发动机部件（100,200）的方法。在代表性的实施例中，组件（100）的冷却通道（102）填充有聚合物，该聚合物在冷却通道（102）中固化以形成预成型材料（110）。然后去除组件（100）的现有外壁层（106,108），从而暴露部分预制件材料（110）。新的外壁层（106-N，108-N）被施加到部件（100）上，并且这可以在冷却流也被施加到部件（100）的同时完成。然后去除预成型坯材料（110）而不破坏新的外壁层（106-N，108-N）。新的外壁层（106-N，108-N）可以通过HVOF工艺或其他方法施加。

22. 发明申请

US20080298975A1 Turbine airfoils with near surface cooling passages and method of making same 有权
标题翻译：具有近表面冷却通道的涡轮翼型及其制造方法
公开(公告)号：US20080298975A1
公开(公告)日：2008-12-04
申请号：US11807389
申请日：2007-05-29
申请人： Allister W. James , Anand A. Kulkarni
发明人： Allister W. James , Anand A. Kulkarni
IPC分类号： F01D5/18 , B23P15/02 , F01D5/08
CPC分类号： F01D5/187 , B23P15/04 , B23P2700/06 , C23C28/321 , C23C28/322 , C23C28/3455 , F01D5/186 , F01D5/288 , F05D2230/30 , F05D2230/90 , F05D2300/611 , Y10T29/49337
摘要： The present invention provides near-surface cooled airfoils that can be made with near-surface cooling passages that are completely free of any leachable or otherwise sacrificial material in the recessed portion of the outer surface of the core. The turbine airfoil comprises a metallic core or substrate having an outer surface and one or a plurality of recessed portions of the outer surface; an intermediate metallic skin or foil having a back surface and a top surface, the back surface of the intermediate skin being bonded to the outer surface of the core such that the recessed portion(s) is sufficiently enclosed so as to form at least one or more near-surface cooling passages or pathways; and at least one or more metallic coatings of a high temperature-resistant metallic material deposited on a top surface of the intermediate skin.
摘要翻译：本发明提供了近表面冷却的翼型件，其可以由在芯体的外表面的凹陷部分中完全没有任何可浸出或以其他方式牺牲的材料的近地表面冷却通道制成。涡轮机翼片包括具有外表面和外表面的一个或多个凹部的金属芯或基板; 具有后表面和顶表面的中间金属表皮或箔，所述中间表皮的后表面结合到所述芯的外表面，使得所述凹陷部分被充分地封闭，从而形成至少一个或多个更接近地面的冷却通道或路径; 以及沉积在中间皮肤的顶表面上的耐高温金属材料的至少一种或多种金属涂层。

23. 发明授权

US08770930B2 Joining mechanism and method for interlocking modular turbine engine component with a split ring 有权
标题翻译：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
申请人： Gary B. Merrill , Allister W. James , Iain A. Fraser
发明人： Gary B. Merrill , Allister W. James , Iain A. Fraser
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）。

24. 发明申请

US20110142684A1 Turbine Engine Airfoil and Platform Assembly 有权
标题翻译：涡轮发动机翼型和平台组件
公开(公告)号：US20110142684A1
公开(公告)日：2011-06-16
申请号：US12638034
申请日：2009-12-15
申请人： Christian X. Campbell , Allister W. James , Jay A. Morrison
发明人： Christian X. Campbell , Allister W. James , Jay A. Morrison
IPC分类号： F01D5/30 , B23P15/04
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。

25. 发明授权

US07905016B2 System for forming a gas cooled airfoil for use in a turbine engine 有权
标题翻译：用于形成用于涡轮发动机的气冷翼的系统
公开(公告)号：US07905016B2
公开(公告)日：2011-03-15
申请号：US11784986
申请日：2007-04-10
申请人： Allister W. James , Douglas J. Arrell
发明人： Allister W. James , Douglas J. Arrell
IPC分类号： B23P15/02
CPC分类号： B23P15/04 , B22F3/1146 , B22F5/04 , B22F7/006 , B22F2003/242 , B22F2003/244 , B22F2003/248 , B22F2998/10 , F01D5/147 , F01D25/12 , F05D2230/31 , F05D2230/90 , F05D2260/20 , F05D2260/203 , F05D2300/611 , Y10T29/49336 , Y10T29/49337 , B22F3/1125 , B22F3/15 , B22F3/24
摘要： A turbine airfoil system for forming a turbine airfoil that is usable in a turbine engine. The airfoil may be formed from a porous material shaped into an outer airfoil shape. The porous material may include an inner central spar capable of supporting the turbine airfoil an outer porous region and an outer coating. The porous material facilitates efficient cooling of the turbine airfoil.
摘要翻译：一种用于形成可用于涡轮发动机的涡轮机翼型的涡轮机翼型系统。翼型件可以由成形为外翼型的多孔材料形成。多孔材料可以包括能够支撑涡轮机翼面外部多孔区域和外部涂层的内部中心翼梁。多孔材料有助于涡轮机翼型的有效冷却。

26. 发明申请

US20100028163A1 Injection Molded Component 有权
标题翻译：注塑成型
公开(公告)号：US20100028163A1
公开(公告)日：2010-02-04
申请号：US12183185
申请日：2008-07-31
申请人： Allister W. James , Douglas J. Arrell
发明人： Allister W. James , Douglas J. Arrell
IPC分类号： F04D29/58 , B23P15/04
CPC分类号： C22C19/03 , C22C19/07 , Y10T29/4932 , Y10T428/12014 , Y10T428/12063
摘要： An intermediate component includes a first wall member, a leachable material layer, and a precursor wall member. The first wall member has an outer surface and first connecting structure. The leachable material layer is provided on the first wall member outer surface. The precursor wall member is formed adjacent to the leachable material layer from a metal powder mixed with a binder material, and includes second connecting structure.
摘要翻译：中间组分包括第一壁构件，可浸出材料层和前体壁构件。第一壁构件具有外表面和第一连接结构。可浸出材料层设置在第一壁构件外表面上。前体壁构件由与粘合剂材料混合的金属粉末相邻于可浸出材料层形成，并且包括第二连接结构。

27. 发明申请

US20090041615A1 Corrosion Resistant Alloy Compositions with Enhanced Castability and Mechanical Properties 审中-公开
标题翻译：具有增强铸造性和机械性能的耐腐蚀合金组合物
公开(公告)号：US20090041615A1
公开(公告)日：2009-02-12
申请号：US12173983
申请日：2008-07-16
申请人： Allister W. James , Gerhard E. Fuchs , Douglas J. Arrell
发明人： Allister W. James , Gerhard E. Fuchs , Douglas J. Arrell
IPC分类号： C22C19/05
CPC分类号： C22C19/056 , C22C19/057 , C22C30/00
摘要： Disclosed are novel nickel-base alloy compositions that may be cast as a single crystal or directionally solidified alloy consisting essentially of, by weight: 8-12% Cr, 10-14% Co, 0.3-0.9% Mo, 3-7% W, 2-8% Ta, 2.0-5.5% Al, 1.5-5.0% Ti, up to 2% Nb, less than 0.1% B, less than 0.1% Zr, 0.05-0.15% C, less than 0.5% Hf, 2-4% Re, 0.05-0.2% Si, up to 0.015% S, up to 0.1% La, up to 0.1% Y, up to 0.1% Ce, up to 0.1% Nd, up to 0.1% Dy, up to 0.1% Pr, up to 0.1% Gd, balance is Ni, and wherein (La+Y+Ce+Nd+Dy+Pr+Gd) is 0.001-0.1%. The compositions for the nickel-base superalloy have a balance between oxidation resistance, corrosion resistance, castability, and mechanical properties, such as creep resistance and thermo-mechanical fatigue resistance.
摘要翻译：公开了可以铸造为单晶或定向凝固合金的新型镍基合金组合物，其基本上由以重量计：8-12％Cr，10-14％Co，0.3-0.9％Mo，3-7％W ，2-8％Ta，2.0-5.5％Al，1.5-5.0％Ti，至多2％Nb，小于0.1％B，小于0.1％Zr，0.05-0.15％C，小于0.5％Hf，2 -4％Re，0.05-0.2％Si，至多0.015％S，至多0.1％La，至多0.1％Y，至多0.1％Ce，至多0.1％Nd，至多0.1％Dy，至多0.1 ％Pr，高达0.1％的Gd，余量为Ni，其中（La + Y + Ce + Nd + Dy + Pr + Gd）为0.001-0.1％。镍基超级合金的组合物在抗氧化性，耐腐蚀性，浇铸性和机械性能如抗蠕变性和耐热机械疲劳性之间具有平衡。

28. 发明授权

US07452182B2 Multi-piece turbine vane assembly 有权
标题翻译：多件式涡轮叶片总成
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。

29. 发明申请

US20080253923A1 Superalloy forming highly adherent chromia surface layer 审中-公开
标题翻译：超合金形成高度粘附的氧化铬表面层
公开(公告)号：US20080253923A1
公开(公告)日：2008-10-16
申请号：US11784987
申请日：2007-04-10
申请人： Douglas J. Arrell , Allister W. James
发明人： Douglas J. Arrell , Allister W. James
IPC分类号： C22C19/05
CPC分类号： C22C19/05
摘要： A nickel-based superalloy that forms a chromia scale in an oxidizing environment is disclosed. The alloy provides good oxidation resistance at temperatures below 900° C. in a dry or moist atmosphere. The superalloy is suited for components of gas or steam turbine engines including blades and vanes.
摘要翻译：公开了一种在氧化环境中形成氧化铬垢的镍基超级合金。该合金在干燥或潮湿的气氛中在低于900℃的温度下提供良好的抗氧化性。超级合金适用于包括叶片和叶片的气体或汽轮机发动机的部件。

30. 发明申请

US20080253894A1 Co-forged steel rotor component for steam and gas turbine engines 有权
标题翻译：用于蒸汽和燃气涡轮发动机的共锻钢转子部件
公开(公告)号：US20080253894A1
公开(公告)日：2008-10-16
申请号：US11784988
申请日：2007-04-10
申请人： Douglas J. Arrell , Allister W. James
发明人： Douglas J. Arrell , Allister W. James
IPC分类号： F01D5/02 , B23P15/00
CPC分类号： B23P15/006 , B21J1/00 , B21K1/32 , B21K3/00 , F01D5/02 , Y10T29/4932 , Y10T29/49321
摘要： A method of forming a rotor for a turbine engine such that the rotor is formed of two materials including: an outer ring formed from a first steel material, and a disk formed from a second material, such as a low alloy steel, having a larger thermal expansion coefficient than the first material forming the inner disk. The ring may include an inner aperture having a conical shape, and the disk may have an outer surface with a conical shape and a diameter with a portion that is larger than a portion of the ring. The ring may be heated such that the aperture expands to a size greater than the largest diameter of the inner disk. The ring may be positioned over the disk and allowed to cool to allow the ring to be attached to the disk. The ring and disk may then be co-forged.
摘要翻译：一种形成用于涡轮发动机的转子的方法，使得转子由两种材料形成，包括：由第一钢材形成的外圈和由诸如低合金钢的第二材料形成的盘，其具有较大的热膨胀系数比形成内盘的第一种材料高。环可以包括具有圆锥形状的内孔，并且盘可以具有圆锥形的外表面和具有大于环的一部分的部分的直径。可以加热环，使得孔扩大到比内盘最大直径大的尺寸。环可以定位在盘上并允许冷却以允许环附接到盘。然后可以共同锻造环和盘。

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