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1. 发明授权

US08070448B2 Spacers and turbines 有权
标题翻译：隔板和涡轮机
公开(公告)号：US08070448B2
公开(公告)日：2011-12-06
申请号：US12261305
申请日：2008-10-30
申请人： Mark C. Morris , Milton Ortiz , David Waldman , James Kroeger
发明人： Mark C. Morris , Milton Ortiz , David Waldman , James Kroeger
IPC分类号： F04D29/34
CPC分类号： F01D11/008 , F05D2240/81 , F05D2260/201 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： Spacers and turbines are provided. In an embodiment, and by way of example only, a spacer includes a strip, a first retention flange, and a second retention flange. The strip has a first edge, a second edge, and an impingement surface, and the impingement surface extends axially along the strip between the first edge and the second edge and is substantially flat. The first retention flange is recessed relative to the impingement surface and extends away from the first edge of the strip. The second retention flange is recessed relative to the impingement surface and extends away from the second edge of the strip.
摘要翻译：提供隔板和涡轮机。在一个实施例中，仅作为示例，间隔件包括条带，第一保持凸缘和第二保持凸缘。带材具有第一边缘，第二边缘和冲击表面，并且冲击表面沿第一边缘和第二边缘之间的条带轴向延伸并且基本上是平坦的。第一保持凸缘相对于冲击表面凹陷并且远离带的第一边缘延伸。第二保持凸缘相对于冲击表面凹陷并且远离带的第二边缘延伸。

2. 发明申请

US20060065383A1 Rapid prototype casting 有权
标题翻译：快速原型铸造
公开(公告)号：US20060065383A1
公开(公告)日：2006-03-30
申请号：US10949082
申请日：2004-09-24
申请人： Milton Ortiz , Malak Malak , Steve Halfmann
发明人： Milton Ortiz , Malak Malak , Steve Halfmann
IPC分类号： B22C9/04 , B22D46/00
CPC分类号： B22C9/04 , B22C7/00 , B22C9/24 , B33Y80/00
摘要： Methods for rapid prototype casting metal components, wherein the metal components are cast in a secondary ceramic mold, the secondary ceramic mold is cast in a primary mold, and the primary mold is formed by rapid prototyping or rapid manufacturing. The secondary ceramic mold may comprise a one-piece integral shell and core(s), and the metal components may have at least one hollow portion or void therein, such as a hollow airfoil for a gas turbine engine.
摘要翻译：用于快速成型铸造金属部件的方法，其中金属部件在二次陶瓷模具中铸造，二次陶瓷模具铸造在初级模具中，并且初级模具通过快速成型或快速制造形成。二次陶瓷模具可以包括一体式的整体壳体和芯部，并且金属部件可以在其中具有至少一个中空部分或空隙，例如用于燃气涡轮发动机的中空翼型件。

3. 发明授权

US06582779B2 Silicon nitride components with protective coating 失效
标题翻译：氮化硅组分与保护涂层
公开(公告)号：US06582779B2
公开(公告)日：2003-06-24
申请号：US09371826
申请日：1999-08-11
申请人： Chien-Wei Li , Derek Raybould , Milton Ortiz , Thomas Edward Strangman
发明人： Chien-Wei Li , Derek Raybould , Milton Ortiz , Thomas Edward Strangman
IPC分类号： C23C1430
CPC分类号： C23C16/405 , C04B35/584 , C04B35/6263 , C04B41/009 , C04B41/52 , C04B41/89 , C04B2235/3213 , C04B2235/3225 , C04B2235/3227 , C04B2235/3826 , C04B2235/483 , C04B2235/616 , C04B2235/656 , C04B2235/77 , C23C26/00 , F01D5/284 , F01D5/288 , C04B41/0072 , C04B41/4517 , C04B41/4539 , C04B41/4578 , C04B41/4582 , C04B41/4596 , C04B41/5066 , C04B41/4515 , C04B41/4535 , C04B41/4554 , C04B41/457 , C04B41/5059 , C04B41/4519 , C04B41/4529 , C04B41/455 , C04B41/5027 , C04B41/4523 , C04B41/522
摘要： A turbomachine component includes a silicon nitride substrate and a multi-layer coating bonded to the substrate. The coating includes an interlayer of porous fibrous silicon nitride having a density of between 85-98%. The coating also includes an outer layer formed of an oxide compound, preferably tantalum oxide, that is applied by Electron Beam-Physical Vapor Deposition. The combination of the silicon nitride interlayer and tantalum oxide outer layer serves to protect the substrate from the adverse affects of oxidation, impact by foreign objects and extreme operating temperatures.
摘要翻译：涡轮机组件包括氮化硅衬底和结合到衬底的多层涂层。涂层包括密度在85-98％之间的多孔纤维状氮化硅夹层。该涂层还包括由氧化物化合物形成的外层，优选氧化钽，其通过电子束物理气相沉积施加。氮化硅中间层和氧化钽外层的组合用于保护衬底免受氧化的不利影响，异物的冲击和极端的工作温度。

4. 发明申请

US20120156044A1 BI-CAST TURBINE ROTOR DISKS AND METHODS OF FORMING SAME 有权
标题翻译：双风轮转子盘及其形成方法
公开(公告)号：US20120156044A1
公开(公告)日：2012-06-21
申请号：US12973424
申请日：2010-12-20
申请人： Milton Ortiz
发明人： Milton Ortiz
IPC分类号： F01D5/30 , B22C7/00 , B22C9/00 , B22D23/00 , B22D25/02
CPC分类号： B29D99/0025 , B22C9/02 , B22D19/00 , F01D5/30 , F01D5/34 , F05D2230/21 , F05D2230/236 , F05D2300/175 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A bi-cast turbine rotor disk and method of forming the same are provided. The disk includes a ring and a blade. The ring comprises a superalloy that includes a plurality of elements, and the blade extends from the ring. The blade comprises a non-metallic ceramic matrix composite, and at least one element from the superalloy of the ring is diffused into the non-metallic ceramic matrix composite of the blade.
摘要翻译：提供了一种双流型涡轮转子盘及其制造方法。盘包括一个环和一个叶片。该环包括包括多个元件的超级合金，并且该刀片从该环延伸。叶片包括非金属陶瓷基复合材料，并且来自环的超合金的至少一种元素被扩散到叶片的非金属陶瓷基复合材料中。

5. 发明申请

US20100111699A1 SPACERS AND TURBINES 有权
标题翻译：间隔和涡轮
公开(公告)号：US20100111699A1
公开(公告)日：2010-05-06
申请号：US12261305
申请日：2008-10-30
申请人： Mark C. Morris , Milton Ortiz , David Waldman , James Kroeger
发明人： Mark C. Morris , Milton Ortiz , David Waldman , James Kroeger
IPC分类号： F01D5/30
CPC分类号： F01D11/008 , F05D2240/81 , F05D2260/201 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： Spacers and turbines are provided. In an embodiment, and by way of example only, a spacer includes a strip, a first retention flange, and a second retention flange. The strip has a first edge, a second edge, and an impingement surface, and the impingement surface extends axially along the strip between the first edge and the second edge and is substantially flat. The first retention flange is recessed relative to the impingement surface and extends away from the first edge of the strip. The second retention flange is recessed relative to the impingement surface and extends away from the second edge of the strip
摘要翻译：提供隔板和涡轮机。在一个实施例中，仅作为示例，间隔件包括条带，第一保持凸缘和第二保持凸缘。带材具有第一边缘，第二边缘和冲击表面，并且冲击表面沿第一边缘和第二边缘之间的条带轴向延伸并且基本上是平坦的。第一保持凸缘相对于冲击表面凹陷并且远离带的第一边缘延伸。第二保持凸缘相对于冲击表面凹陷并且远离带的第二边缘延伸

6. 发明授权

US06974308B2 High effectiveness cooled turbine vane or blade 有权
标题翻译：高效冷却涡轮叶片或叶片
公开(公告)号：US06974308B2
公开(公告)日：2005-12-13
申请号：US09992250
申请日：2001-11-14
申请人： Steve H. Halfmann , Yong W. Kim , Mark C. Morris , Milton Ortiz , David R. Pack , Craig A. Wilson
发明人： Steve H. Halfmann , Yong W. Kim , Mark C. Morris , Milton Ortiz , David R. Pack , Craig A. Wilson
IPC分类号： F01D5/18 , F01D5/16 , F01D9/06
CPC分类号： B22C9/04 , B22C9/103 , F01D5/187 , F05D2230/21 , F05D2260/202 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A robust multiple-walled, multi-pass, high cooling effectiveness cooled turbine vane or blade designed for ease of manufacturability, minimizes cooling flows on highly loaded turbine rotors. The vane or blade design allows the turbine inlet temperature to increase over current technology levels while simultaneously reducing turbine cooling to low levels. A multi-wall cooling system is described, which meets the inherent conflict to maximize the flow area of the cooling passages while retaining the required section thickness to meet the structural requirements. Independent cooling circuits for the vane or blade's pressure and suction surfaces allow the cooling of the airfoil surfaces to be tailored to specific heat load distributions (that is, the pressure surface circuit is an independent forward flowing serpentine while the suction surface is an independent rearward flowing serpentine). The cooling air for the independent circuits is supplied through separate passages at the base of the vane or blade. The cooling air follows intricate passages to feed the serpentine thin outer wall passages, which incorporate pin fins, turbulators, etc. These passages, while satisfying the aero/thermal/stress requirements, are of a manufacturing configuration that may be cast with single crystal materials using conventional casting techniques.
摘要翻译：为了便于制造而设计的强大的多层，多通，高冷却效率的冷却涡轮叶片或叶片，使得高负载涡轮转子上的冷却流量最小化。叶片或叶片设计允许涡轮进口温度升高超过当前技术水平，同时将涡轮机冷却降低到低水平。描述了一种多壁冷却系统，其满足固有的冲突，以最大化冷却通道的流动面积，同时保持所需的部分厚度以满足结构要求。用于叶片或叶片的压力和吸力表面的独立冷却回路允许翼型表面的冷却根据特定的热负荷分布进行调整（即，压力表面回路是独立的向前流动的蛇形管，而吸力表面是独立的向后流动蛇纹石）。用于独立回路的冷却空气通过在叶片或叶片的基部处的分开的通道供应。冷却空气跟随复杂的通道，以供入蛇形薄壁外壁通道，这些通道包括销翅片，湍流器等。这些通道在满足航空/热/应力要求的同时，具有可以用单晶材料铸造的制造结构使用常规铸造技术。

7. 发明授权

US06478535B1 Thin wall cooling system 有权
公开(公告)号：US06478535B1
公开(公告)日：2002-11-12
申请号：US09848844
申请日：2001-05-04
申请人： Vincent Chung , Milton Ortiz , Kin Poon
发明人： Vincent Chung , Milton Ortiz , Kin Poon
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2260/202 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： A thin wall cooling system has multiple in-wall channels traversing a thin wall structure such as the wall of a gas turbine engine blade or vane. The blade has a hollow interior that may be divided into multiple cavities. Coolant is introduced into an entry opening of each in-wall channel and then discharged through exit openings into the vane cavities. The coolant then exits the cavities by through wall channels to discharge the coolant to form a cool air film on the external surface of the blade. This combination allows improved cooling control for structures that experience an elevated temperature environment, as for example, the flow of hot gas across the exterior surface of a gas turbine engine blade.

8. 发明授权

US07448433B2 Rapid prototype casting 有权
标题翻译：快速原型铸造
公开(公告)号：US07448433B2
公开(公告)日：2008-11-11
申请号：US10949082
申请日：2004-09-24
申请人： Milton Ortiz , Malak F. Malak , Steve H. Halfmann
发明人： Milton Ortiz , Malak F. Malak , Steve H. Halfmann
IPC分类号： B22C9/00
CPC分类号： B22C9/04 , B22C7/00 , B22C9/24 , B33Y80/00
摘要： Methods for rapid prototype casting metal components, wherein the metal components are cast in a secondary ceramic mold, the secondary ceramic mold is cast in a primary mold, and the primary mold is formed by rapid prototyping or rapid manufacturing. The secondary ceramic mold may comprise a one-piece integral shell and core(s), and the metal components may have at least one hollow portion or void therein, such as a hollow airfoil for a gas turbine engine.
摘要翻译：用于快速成型铸造金属部件的方法，其中金属部件在二次陶瓷模具中铸造，二次陶瓷模具铸造在初级模具中，并且初级模具通过快速成型或快速制造形成。二次陶瓷模具可以包括一体式的整体壳体和芯部，并且金属部件可以在其中具有至少一个中空部分或空隙，例如用于燃气涡轮发动机的中空翼型件。

9. 发明授权

US08801388B2 Bi-cast turbine rotor disks and methods of forming same 有权
标题翻译：双流涡轮转子盘及其形成方法
公开(公告)号：US08801388B2
公开(公告)日：2014-08-12
申请号：US12973424
申请日：2010-12-20
申请人： Milton Ortiz
发明人： Milton Ortiz
IPC分类号： F01D5/28
CPC分类号： B29D99/0025 , B22C9/02 , B22D19/00 , F01D5/30 , F01D5/34 , F05D2230/21 , F05D2230/236 , F05D2300/175 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A bi-cast turbine rotor disk and method of forming the same are provided. The disk includes a ring and a blade. The ring comprises a superalloy that includes a plurality of elements, and the blade extends from the ring. The blade comprises a non-metallic ceramic matrix composite, and at least one element from the superalloy of the ring is diffused into the non-metallic ceramic matrix composite of the blade.
摘要翻译：提供了一种双流型涡轮转子盘及其制造方法。盘包括一个环和一个叶片。该环包括包括多个元件的超级合金，并且该刀片从该环延伸。叶片包括非金属陶瓷基复合材料，并且来自环的超合金的至少一种元素被扩散到叶片的非金属陶瓷基复合材料中。

10. 发明申请

US20050131570A1 Procedures for rapid build and improved surface characteristics in layered manufacture 审中-公开
标题翻译：分层制造快速构建和改善表面特性的程序
公开(公告)号：US20050131570A1
公开(公告)日：2005-06-16
申请号：US10762449
申请日：2004-01-20
申请人： Vikram Jamalabad , Charles Gasdaska , Milton Ortiz
发明人： Vikram Jamalabad , Charles Gasdaska , Milton Ortiz
IPC分类号： B29C67/00 , G06F19/00
CPC分类号： B28B3/10 , B29C64/106 , B29C64/40
摘要： Methods for improving layered manufacturing techniques to improve an objects' surface properties and shorten manufacturing time for support structures. One aspect of the invention forms surfaces having reduced or no concavities between layers having improved crack resistance. One method deposits alternate, surface improvement material on each layer near the future location of the main material surface, followed by deposition of the main material, the edges of which conform to the previously deposited and solidified alternate material. In this method, the center of the main material layers can be concave rather than the interlayer regions. Another aspect of the invention provides removable structures to support the deposition of main material. The support structures provide support over main material cavities for depositing the material to form the cavity ceilings, while minimizing the time and material required to build the support structures. Minimized support structures include structures formed as columns supported by the cavity floor and angle braces to supported by the cavity walls. Some supports are supported by the side wall but not the floor, and other by the floor and not the side walls.
摘要翻译：改进分层制造技术以改善物体表面性能并缩短支撑结构的制造时间的方法。本发明的一个方面形成具有减小的或不具有改善的抗裂性的层之间的凹面的表面。一种方法在主材料表面的未来位置附近的每个层上沉积交替的表面改性材料，随后沉积主要材料，其边缘符合先前沉积和固化的替代材料。在该方法中，主材料层的中心可以是凹形而不是层间区域。本发明的另一方面提供了用于支撑主材料沉积的可移除结构。支撑结构在主材料空腔上提供支撑，用于沉积材料以形成腔体天花板，同时最小化构建支撑结构所需的时间和材料。最小化的支撑结构包括由腔体支撑的柱形成的结构和由腔壁支撑的角撑架。一些支撑件由侧壁支撑，但不由地板支撑，而另一些由地板而不是侧壁支撑。

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