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1. 发明授权

US07789621B2 Gas turbine engine airfoil 有权
标题翻译：燃气涡轮发动机翼型
公开(公告)号：US07789621B2
公开(公告)日：2010-09-07
申请号：US11475650
申请日：2006-06-27
申请人： Douglas David Dierksmeier , Jeffrey F. Rhodes , Tab Michael Heffernan
发明人： Douglas David Dierksmeier , Jeffrey F. Rhodes , Tab Michael Heffernan
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/187 , F01D5/284 , F05D2230/60 , F05D2230/64 , F05D2300/607 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： A gas turbine engine airfoil including at least one outer tile coupled to a supporting member. The outer tile is coupled to the supporting member by a pin passing though the supporting member and the outer tile.
摘要翻译：一种燃气涡轮发动机翼型件，其包括联接到支撑构件的至少一个外部瓦片。外部瓦片通过穿过支撑构件和外部瓦片的销钉联接到支撑构件。

2. 发明授权

US6003754A Airfoil for a gas turbine engine and method of manufacture 失效
标题翻译：用于燃气涡轮发动机的翼型及其制造方法
公开(公告)号：US6003754A
公开(公告)日：1999-12-21
申请号：US954907
申请日：1997-10-21
申请人： Jeffrey F. Rhodes
发明人： Jeffrey F. Rhodes
IPC分类号： B22C7/00 , B22C7/02 , B22C9/04 , B22C9/06 , B23K20/02 , B23K31/02 , B23K37/04 , B23K20/00
CPC分类号： B23K31/02 , B22C7/00 , B22C7/02 , B22C9/04 , B22C9/06 , B23K20/02 , B23K37/0443 , B23K2201/001 , Y10T29/49336
摘要： A fabricated gas turbine engine component and method of manufacturing. In one embodiment the component having a structural member with a cover member metalurgically bonded thereto. The bonding of the cover member being controlled by an apparatus that sequentially applies a substantially non-unifrom bonding load across the components radius of curvature. The patterns utilized in the casting process are formed in one embodiment to a precision preformed geometry by a closed die forming operation.
摘要翻译：一种制造的燃气涡轮发动机部件及其制造方法。在一个实施例中，所述部件具有结构部件，所述结构部件具有与其结合的盖部件。覆盖构件的结合由一种装置控制，该装置在整个曲率半径上依次施加基本上非单一的结合载荷。在一个实施例中，在铸造工艺中使用的图案通过封闭的模具形成操作形成精确的预成型几何形状。

3. 发明授权

US5797725A Gas turbine engine vane and method of manufacture 失效
标题翻译：燃气轮机发动机叶片及其制造方法
公开(公告)号：US5797725A
公开(公告)日：1998-08-25
申请号：US862837
申请日：1997-05-23
申请人： Jeffrey F. Rhodes
发明人： Jeffrey F. Rhodes
IPC分类号： F01D9/04 , F04D29/44
CPC分类号： B23P6/005 , F01D9/042 , F05D2230/60
摘要： A gas turbine engine vane and method of manufacture. In one form of the present invention a vane is non destructively removeable from a vane segment to allow individual components to be replaced. The vane and endwalls are coupled together by a retainer that is formed in place between the vane and the endwall and that can be removed by conventional techniques. In one form the retainer fills a pair of corresponding grooves in the vane and endwall member so as to mechanically couple the components together and minimize fluid leakage therebetween. The retainer being nonmetallurgically coupled to the vane and endwall member. A portion of the vane being allowed to move relative to the endwall in response to thermal conditions.
摘要翻译：一种燃气轮机发动机叶片及其制造方法。在本发明的一种形式中，叶片不能从叶片段破坏性地移除，以允许更换各个部件。叶片和端壁通过保持器联接在一起，该保持器形成在叶片和端壁之间的适当位置，并且可以通过常规技术去除。在一种形式中，保持器填充叶片和端壁构件中的一对对应的凹槽，以便将部件机械地连接在一起并使其间的流体泄漏最小化。保持器非金属地联接到叶片和端壁构件。响应于热条件，允许叶片的一部分相对于端壁移动。

4. 发明授权

US10060264B2 Gas turbine engine and cooled flowpath component therefor 有权
公开(公告)号：US10060264B2
公开(公告)日：2018-08-28
申请号：US13337103
申请日：2011-12-24
申请人： Corina Moga , Jerry Layne , Jeffrey F. Rhodes
发明人： Corina Moga , Jerry Layne , Jeffrey F. Rhodes
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/147 , F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/126 , F05D2240/304 , F05D2250/18 , F05D2260/202 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： Apparatus and systems for a cooled gas turbine engine flowpath component are disclosed. In some embodiments, the flowpath component includes a spar and a coversheet. The spar may include a suction-side wall extending from a leading edge to a trailing edge and a pressure-side wall extending from the leading edge to the trailing edge, each wall having an outer surface. The coversheet may be positioned on the spar to at least partially enclose the spar, the coversheet having an engagement surface positioned to face the outer surface of the suction-side wall and the outer surface of the pressure-side wall. The spar and the coversheet cooperate to form a number of passageways configured to cool the flowpath component.

5. 发明授权

US06224339B1 High temperature airfoil 失效
标题翻译：高温翼型
公开(公告)号：US06224339B1
公开(公告)日：2001-05-01
申请号：US09111651
申请日：1998-07-08
申请人： Jeffrey F. Rhodes , Jon D. Harvey
发明人： Jeffrey F. Rhodes , Jon D. Harvey
IPC分类号： F01D518
CPC分类号： F01D5/288 , F01D5/186 , F01D5/187 , F01D5/284 , F01D5/3084 , F01D11/008 , F16B2200/30 , Y02T50/67 , Y02T50/671 , Y02T50/676 , Y10T29/49337 , Y10T29/49826 , Y10T403/362 , Y10T403/7015
摘要： A high temperature repairable airfoil having a plurality of flow path cover tiles coupled to a single crystal spar member. In one embodiment, the plurality of flow path cover tiles include an attachment portion that is received within a groove formed in the outer surface of the spar. The attachment portion slides into a retaining feature within the groove so as to limit movement of the plurality of flow path cover tiles. Upon rotation of the airfoil, the plurality of flow path cover tiles become centrifugally loaded with a portion of the spar member. In one embodiment, the plurality of flow path cover tiles are formed of a material selected from the group consisting of ceramics, intermetallic, and thermal barrier coated single crystal alloy material.
摘要翻译：一种高温可修复翼型件，其具有联接到单晶翼梁构件的多个流动路径覆盖瓦。在一个实施例中，多个流动通道盖瓦片包括接收在形成在翼梁的外表面中的凹槽内的附接部分。附接部分滑入凹槽内的保持特征，以便限制多个流动通道盖瓦片的移动。在翼型件旋转时，多个流路覆盖瓦片被离心地装载在翼梁件的一部分上。在一个实施例中，多个流路盖瓦由选自陶瓷，金属间隔层和隔热涂层单晶合金材料的材料形成。

6. 发明授权

US6003756A Airfoil for gas a turbine engine and method of manufacture 有权
标题翻译：气体翼型用于涡轮发动机及其制造方法
公开(公告)号：US6003756A
公开(公告)日：1999-12-21
申请号：US276059
申请日：1999-03-25
申请人： Jeffrey F. Rhodes
发明人： Jeffrey F. Rhodes
IPC分类号： B22C7/00 , B22C7/02 , B22C9/04 , B22C9/06 , B23K20/02 , B23K31/02 , B23K37/04 , B21D39/00 , B23K20/00 , B27D1/00
CPC分类号： B23K31/02 , B22C7/00 , B22C7/02 , B22C9/04 , B22C9/06 , B23K20/02 , B23K37/0443 , B23K2201/001 , Y10T29/49336
摘要： A fabricated gas turbine engine component and method of manufacturing. In one embodiment the component having a structural member with a cover member metalurgically bonded thereto. The bonding of the cover member being controlled by an apparatus that sequentially applies a substantially non-unifrom bonding load across the components radius of curvature. The patterns utilized in the casting process are formed in one embodiment to a precision preformed geometry by a closed die forming operation.
摘要翻译：一种制造的燃气涡轮发动机部件及其制造方法。在一个实施例中，所述部件具有结构部件，所述结构部件具有与其结合的盖部件。覆盖构件的结合由一种装置控制，该装置在整个曲率半径上依次施加基本上非单一的结合载荷。在一个实施例中，在铸造工艺中使用的图案通过封闭模具形成操作形成精密预成形几何形状。

7. 发明申请

US20120201653A1 GAS TURBINE ENGINE AND COOLED FLOWPATH COMPONENT THEREFOR 审中-公开
标题翻译：燃气涡轮发动机和冷却流量组件
公开(公告)号：US20120201653A1
公开(公告)日：2012-08-09
申请号：US13337103
申请日：2011-12-24
申请人： Corina Moga , Jerry Layne , Jeffrey F. Rhodes
发明人： Corina Moga , Jerry Layne , Jeffrey F. Rhodes
IPC分类号： F01D9/02 , F01D25/12
CPC分类号： F01D5/147 , F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/126 , F05D2240/304 , F05D2250/18 , F05D2260/202 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is a unique cooled gas turbine engine flowpath component. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and cooled gas turbine engine flowpath components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
摘要翻译：本发明的一个实施例是独特的燃气涡轮发动机。本发明的另一个实施例是独特的冷却燃气涡轮发动机流路组件。其他实施例包括用于燃气涡轮发动机和冷却燃气涡轮发动机流路部件的装置，系统，装置，硬件，方法和组合。本申请的其它实施例，形式，特征，方面，益处和优点将从本文提供的描述和附图中变得显而易见。

8. 发明申请

US20120189427A1 GAS TURBINE ENGINE FLOW PATH MEMBER 有权
标题翻译：气体涡轮发动机流路成员
公开(公告)号：US20120189427A1
公开(公告)日：2012-07-26
申请号：US13335276
申请日：2011-12-22
申请人： Okey Kwon , Jeffrey F. Rhodes
发明人： Okey Kwon , Jeffrey F. Rhodes
IPC分类号： F01D25/12 , F01D1/00
CPC分类号： F01D5/187 , F01D5/20 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine flow path member is disclosed which includes an extending end portion capable of contacting a surface of the turbine engine. The flow path member includes openings to pass a cooling fluid to cool the extending end portion. The flow path member, furthermore, can be made using a variety of approaches. To set forth just two non-limiting examples, the flow path member can be cast and it can be a laminated construction.
摘要翻译：公开了一种燃气涡轮发动机流路构件，其包括能够接触涡轮发动机的表面的延伸端部。流路构件包括通过冷却流体以冷却延伸端部的开口。此外，流路构件可以使用各种方法制成。为了仅举出两个非限制性实例，流路构件可以铸造并且其可以是层压结构。

9. 发明申请

US20100074759A1 GAS TURBINE ENGINE AIRFOIL 有权
标题翻译：气体涡轮发动机气翼
公开(公告)号：US20100074759A1
公开(公告)日：2010-03-25
申请号：US11475650
申请日：2006-06-27
申请人： Douglas David Dierksmeier , Jeffrey F. Rhodes , Tab Michael Heffernan
发明人： Douglas David Dierksmeier , Jeffrey F. Rhodes , Tab Michael Heffernan
IPC分类号： F01D5/28 , F01D5/14
CPC分类号： F01D5/147 , F01D5/187 , F01D5/284 , F05D2230/60 , F05D2230/64 , F05D2300/607 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： A gas turbine engine airfoil including at least one outer tile coupled to a supporting member. The outer tile is coupled to the supporting member by a pin passing though the supporting member and the outer tile.
摘要翻译：一种燃气涡轮发动机翼型件，其包括联接到支撑构件的至少一个外部瓦片。外部瓦片通过穿过支撑构件和外部瓦片的销钉联接到支撑构件。

10. 发明授权

US5152667A Cooled wall structure especially for gas turbine engines 失效
标题翻译：特别适用于燃气轮机的冷却墙结构
公开(公告)号：US5152667A
公开(公告)日：1992-10-06
申请号：US730729
申请日：1991-07-16
申请人： Edward R. Turner , Jeffrey F. Rhodes , Larry A. Junod
发明人： Edward R. Turner , Jeffrey F. Rhodes , Larry A. Junod
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/201
摘要： A cooled wall structure including a hot side, a cold side, a linear slot opening through the hot side, a plurality of diffusion chambers below the hot side separated therefrom by relatively thin bridge sections of the wall structure and arrayed in checkerboard fashion on opposite sides of the linear slot and opening into the linear slot through the sidewalls thereof, and a plurality of passages from the cold side to each of the diffusion chambers. The cold side is exposed to coolant gas under pressure and the passages are aimed at the bridge sections so that jet of cooling gas issuing from the passages impinge against the bridge section for convection cooling the hot side. The bridge sections prevent direct penetration of the coolant gas jets into the environment adjacent the hot side. The coolant gas flows from the diffusion chambers into the linear slots and from the linear slots over the hot side to form on the latter a coolant film or blanket.
摘要翻译：冷壁结构，其包括热侧，冷侧，通过热侧的直线槽，在热侧下方的多个扩散室，通过壁结构的相对较薄的桥接部分与其隔开，并且在相对侧以棋盘方式排列并且通过其侧壁开口到直线槽中，以及从冷侧到每个扩散室的多个通道。冷侧在压力下暴露于冷却剂气体，并且通道朝向桥接部分，使得从通道发出的冷却气体射流撞击桥接部分以对流冷却热侧。桥接部分防止冷却剂气体射流直接穿入热侧附近的环境中。冷却剂气体从扩散室流入直线槽，并从热侧的线性槽流出，在其上形成冷却剂膜或覆盖层。

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