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1. 发明授权

US08794006B2 Flow sleeve impingement cooling baffles 有权
标题翻译：流动套筒冲击冷却挡板
公开(公告)号：US08794006B2
公开(公告)日：2014-08-05
申请号：US13553076
申请日：2012-07-19
申请人： Jaisukhlal V. Chokshi , Craig F. Smith , Carlos G. Figueroa , Larry C. George
发明人： Jaisukhlal V. Chokshi , Craig F. Smith , Carlos G. Figueroa , Larry C. George
IPC分类号： F02C1/00
CPC分类号： F23R3/08 , F23R3/06 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.
摘要翻译：用于涡轮发动机的燃烧器组件包括燃烧器衬套，流动套筒和挡板环。流动套管围绕燃烧器衬套。在流动套筒和燃烧器衬套之间形成一个环。在流动套筒中形成多排冷却孔。挡板环径向包围燃烧器衬套并且位于环形空间中。

2. 发明授权

US08051662B2 Transition duct assemblies and gas turbine engine systems involving such assemblies 有权
标题翻译：过渡管道组件和涉及这种组件的燃气涡轮发动机系统
公开(公告)号：US08051662B2
公开(公告)日：2011-11-08
申请号：US12368403
申请日：2009-02-10
申请人： Carlos G. Figueroa , Craig F. Smith
发明人： Carlos G. Figueroa , Craig F. Smith
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F01D9/023 , F05D2260/201
摘要： Transition duct assemblies and gas turbine engine systems involving such assemblies are provided. In this regard, a representative a transition duct assembly for a gas turbine engine includes: an impingement sheet having cooling holes formed therethrough, an inlet end and a non-flanged outlet end, the impingement sheet being operative to be positioned about an exterior of a transition duct such that cooling air is directed to flow about the transition duct; the non-flanged outlet end of the impingement sheet being operative to attach the impingement sheet to the transition duct such that the inlet end is positioned adjacent to an intake end of the transition duct and the outlet end is positioned adjacent to an exhaust end of the transition duct.
摘要翻译：提供了涉及这种组件的过渡管道组件和燃气涡轮发动机系统。在这方面，代表性的用于燃气涡轮发动机的过渡管道组件包括：冲击片，其具有穿过其形成的冷却孔，入口端和非凸缘出口端，所述冲击片可操作以围绕过渡管道，使得冷却空气被引导以围绕过渡管道流动; 冲击片的非法兰出口端可操作以将冲击片附接到过渡管道，使得入口端邻近过渡管道的进气端定位，并且出口端定位成邻近于过渡管道的排气端过渡管道

3. 发明授权

US08829457B2 Ultraviolet radiation detector and dosimeter 有权
标题翻译：紫外线辐射探测器和剂量计
公开(公告)号：US08829457B2
公开(公告)日：2014-09-09
申请号：US13418178
申请日：2012-03-12
申请人： Craig F. Smith , Vladimir Ryzhikov , Sergei Naydenov , Dennis Wood , Volodymyr Perevertailo
发明人： Craig F. Smith , Vladimir Ryzhikov , Sergei Naydenov , Dennis Wood , Volodymyr Perevertailo
IPC分类号： G01J1/42 , H01L31/0216 , H01L31/108
CPC分类号： H01L31/108 , G01J1/429 , H01L31/02162
摘要： An ultraviolet radiation dosimeter apparatus for measuring an individual's ultraviolet radiation exposure from incoming ultraviolet rays, including an ultraviolet radiation dosimeter body; an ultraviolet filter in the ultraviolet radiation dosimeter body; a detector semiconductor substrate in the ultraviolet radiation dosimeter body connected to the ultraviolet filter for detecting the incoming ultraviolet rays and producing a signal, the semiconductor substrate made of ZnSe(Te), and a chip in the ultraviolet radiation dosimeter body for receiving the signal and measuring the individual's ultraviolet radiation exposure from the incoming ultraviolet rays.
摘要翻译：一种紫外线辐射剂量计装置，用于测量个体的紫外线辐射暴露量，包括紫外辐射剂量计主体; 紫外线辐射剂量计体内的紫外线过滤器; 紫外线辐射剂量计主体中的检测器半导体衬底，连接到用于检测入射紫外线并产生信号的紫外线过滤器，由ZnSe（Te）制成的半导体衬底和用于接收信号的紫外线辐射剂量计主体中的芯片，从入射的紫外线测量个人的紫外线辐射暴露。

4. 发明授权

US08572979B2 Gas turbine combustor liner cap assembly 有权
标题翻译：燃气轮机燃烧器衬套组件
公开(公告)号：US08572979B2
公开(公告)日：2013-11-05
申请号：US12822607
申请日：2010-06-24
申请人： Craig F. Smith , Hannes A. Alholm , Jonathan J. Eastwood , Dennis J. Duhamel , David A. Burns , Claude I. Barnett, Jr. , Randy J. Danburg , Jeffrey D. Melman , David R. Wiley , Monica Pacheco-Tougas
发明人： Craig F. Smith , Hannes A. Alholm , Jonathan J. Eastwood , Dennis J. Duhamel , David A. Burns , Claude I. Barnett, Jr. , Randy J. Danburg , Jeffrey D. Melman , David R. Wiley , Monica Pacheco-Tougas
IPC分类号： F02C1/00
CPC分类号： F23R3/002 , F23R2900/00017 , F23R2900/00018
摘要： A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate.
摘要翻译：提供燃烧器衬套盖组件以用于燃气轮机的多燃料喷嘴燃烧室。燃烧器衬套组件包括具有多个燃料喷嘴开口的管板和从管板向后延伸的多个开放式预混合管。每个预混管具有前端具有前缘，前端被接收在对应的一个燃料喷嘴开口中。每个预混合管被固定到预混合管前端的前边缘的管板上，例如通过焊接或钎焊冶金结合到管板或螺纹连接到管板中。

5. 发明授权

US08091370B2 Combustor liner cap assembly 有权
标题翻译：燃烧器衬套组件
公开(公告)号：US08091370B2
公开(公告)日：2012-01-10
申请号：US12132285
申请日：2008-06-03
申请人： Richard S. Tuthill , Craig F. Smith
发明人： Richard S. Tuthill , Craig F. Smith
IPC分类号： F02C7/20 , F02C7/08
CPC分类号： F23R3/60 , F23R3/002
摘要： A liner cap assembly is disclosed for use in a gas turbine engine combustor. The assembly includes an outer ring that extends along an axis. Multiple struts are circumferentially arranged about an inner diameter of the outer ring and extend radially inwardly therefrom. A plate is supported by and axially aligned with the struts. The plate includes multiple circumferential openings that support a collar and a premix tube at each of the openings. The plate is arranged between leading and trailing edges of the struts to provide a stiffened liner cap assembly that is robust and resistant to the vibrations typically found in dry low NOx systems.
摘要翻译：公开了一种用于燃气涡轮发动机燃烧器的衬套盖组件。组件包括沿轴线延伸的外环。多个支柱围绕外圈的内径周向地布置并且从其径向向内延伸。板支撑并与支柱轴向对齐。该板包括多个周向开口，其在每个开口处支撑轴环和预混合管。板被布置在支柱的前缘和后缘之间，以提供坚固的并且耐受通常在干燥的低NOx系统中发现的振动的加强的衬套组件。

6. 发明申请

US20110314823A1 GAS TURBINE COMBUSTOR LINER CAP ASSEMBLY 有权
标题翻译：气体涡轮搅拌机衬管总成
公开(公告)号：US20110314823A1
公开(公告)日：2011-12-29
申请号：US12822607
申请日：2010-06-24
申请人： Craig F. Smith , Hannes A. Alholm , Jonathan J. Eastwood , Dennis J. Duhamel , David A. Burns , Claude I. Barnett, JR. , Randy J. Danburg , Jeffrey D. Melman , David R. Wiley , Monica Pacheco-Tougas
发明人： Craig F. Smith , Hannes A. Alholm , Jonathan J. Eastwood , Dennis J. Duhamel , David A. Burns , Claude I. Barnett, JR. , Randy J. Danburg , Jeffrey D. Melman , David R. Wiley , Monica Pacheco-Tougas
IPC分类号： F02C7/22
CPC分类号： F23R3/002 , F23R2900/00017 , F23R2900/00018
摘要： A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate.
摘要翻译：提供燃烧器衬套盖组件以用于燃气轮机的多燃料喷嘴燃烧室。燃烧器衬套组件包括具有多个燃料喷嘴开口的管板和从管板向后延伸的多个开放式预混合管。每个预混管具有前端具有前缘，前端被接收在对应的一个燃料喷嘴开口中。每个预混合管被固定到预混合管前端的前边缘的管板上，例如通过焊接或钎焊冶金结合到管板或螺纹连接到管板中。

7. 发明申请

US20100199677A1 Transition Duct Assemblies and Gas Turbine Engine Systems Involving Such Assemblies 有权
标题翻译：过渡管道组件和涉及这种组件的燃气轮机发动机系统
公开(公告)号：US20100199677A1
公开(公告)日：2010-08-12
申请号：US12368403
申请日：2009-02-10
申请人： Carlos G. Figueroa , Craig F. Smith
发明人： Carlos G. Figueroa , Craig F. Smith
IPC分类号： F23R3/42
CPC分类号： F01D9/023 , F05D2260/201
摘要： Transition duct assemblies and gas turbine engine systems involving such assemblies are provided. In this regard, a representative a transition duct assembly for a gas turbine engine includes: an impingement sheet having cooling holes formed therethrough, an inlet end and a non-flanged outlet end, the impingement sheet being operative to be positioned about an exterior of a transition duct such that cooling air is directed to flow about the transition duct; the non-flanged outlet end of the impingement sheet being operative to attach the impingement sheet to the transition duct such that the inlet end is positioned adjacent to an intake end of the transition duct and the outlet end is positioned adjacent to an exhaust end of the transition duct.
摘要翻译：提供了涉及这种组件的过渡管道组件和燃气涡轮发动机系统。在这方面，代表性的用于燃气涡轮发动机的过渡管道组件包括：冲击片，其具有穿过其形成的冷却孔，入口端和非凸缘出口端，所述冲击片可操作以围绕过渡管道，使得冷却空气被引导以围绕过渡管道流动; 冲击片的非法兰出口端可操作以将冲击片附接到过渡管道，使得入口端邻近过渡管道的进气端定位，并且出口端定位成邻近于过渡管道的排气端过渡管道。

8. 发明申请

US20100031665A1 FLOW SLEEVE IMPINGEMENT COOLING USING A PLENUM RING 有权
标题翻译：流动套管冲压使用环形圈
公开(公告)号：US20100031665A1
公开(公告)日：2010-02-11
申请号：US12176895
申请日：2008-07-21
申请人： Jaisukhlal V. Chokshi , Craig F. Smith , Carlos G. Figueroa
发明人： Jaisukhlal V. Chokshi , Craig F. Smith , Carlos G. Figueroa
IPC分类号： F02C7/12
CPC分类号： F01D5/186 , F02K1/822 , F23R3/002 , F23R3/005 , F23R3/06 , F23R3/54 , F23R2900/03044 , Y02T50/675
摘要： A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes. The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes for directing axial air flow and radial flow chambers for directing radial air flow.
摘要翻译：用于涡轮发动机的燃烧器组件包括燃烧器衬套，流动套管和增压环。流动套筒围绕燃烧器衬套以在燃烧器衬套和流动套筒之间径向形成环形空间。流动套筒具有多排冷却孔。增压环径向包围环形空间中的燃烧器衬套。气室环具有多个用于引导轴向气流的旁通管和用于引导径向气流的径向流动室。

9. 发明申请

US20100000200A1 IMPINGEMENT COOLING DEVICE 有权
标题翻译：冲压冷却装置
公开(公告)号：US20100000200A1
公开(公告)日：2010-01-07
申请号：US12167284
申请日：2008-07-03
申请人： Craig F. Smith
发明人： Craig F. Smith
IPC分类号： F02K99/00
CPC分类号： F23R3/002 , F01D5/186 , F01D9/023 , F05D2260/201 , F23R2900/03044
摘要： An impingement cooling sleeve includes a sleeve body having an inner surface to face a transition duct and an outer surface facing opposite the inner surface. At least one cooling hole is formed within the sleeve body and is used to direct cooling air toward the transition duct. At least one conduit member is attached to the sleeve body and is associated with the at least one cooling hole. The conduit member has a first opening to define an air inlet and a second opening to define an air outlet. In one example, the first opening is spaced apart from the outer surface of the sleeve body by a distance. In one example, the first opening comprises an annular end face surface that defines a plane that is obliquely orientated relative to the outer surface of the sleeve body.
摘要翻译：冲击冷却套筒包括具有面向过渡管道的内表面和面向内表面相对的外表面的套管主体。至少一个冷却孔形成在套筒本体内，用于将冷却空气引向过渡管道。至少一个导管构件附接到套筒主体并且与至少一个冷却孔相关联。导管构件具有限定空气入口的第一开口和用于限定空气出口的第二开口。在一个示例中，第一开口与套管主体的外表面间隔一定距离。在一个示例中，第一开口包括限定相对于套筒本体的外表面倾斜定向的平面的环形端面表面。

10. 发明申请

US20130000310A1 FLOW SLEEVE IMPINGEMENT COOLING BAFFLES 有权
标题翻译：流水冲洗冷却桶
公开(公告)号：US20130000310A1
公开(公告)日：2013-01-03
申请号：US13553076
申请日：2012-07-19
申请人： Jaisukhlal V. Chokshi , Craig F. Smith , Carlos G. Figueroa , Larry C. George
发明人： Jaisukhlal V. Chokshi , Craig F. Smith , Carlos G. Figueroa , Larry C. George
IPC分类号： F02C7/00 , F23R3/26
CPC分类号： F23R3/08 , F23R3/06 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus.
摘要翻译：用于涡轮发动机的燃烧器组件包括燃烧器衬套，流动套筒和挡板环。流动套管围绕燃烧器衬套。在流动套管和燃烧器衬套之间形成有环。在流动套筒中形成多排冷却孔。挡板环径向包围燃烧器衬套并且位于环形空间中。

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