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1. 发明申请

US20130251515A1 THERMAL ISOLATION APPARATUS 有权
标题翻译：热隔离装置
公开(公告)号：US20130251515A1
公开(公告)日：2013-09-26
申请号：US13425029
申请日：2012-03-20
申请人： Donald Earl Floyd , David Martin Johnson
发明人： Donald Earl Floyd , David Martin Johnson
IPC分类号： F01D25/14
CPC分类号： F01D11/18 , F01D9/04 , F05D2300/502
摘要： A thermal isolation apparatus is provided and includes an annular casing surrounding a turbine bucket stage and defining an annular recess from an interior facing surface thereof, an annular shroud disposed within the casing to provide for a predefined clearance about rotating bucket tips of the turbine bucket stage, the shroud including an annular main member and an annular flange extending from an outwardly facing surface of the main member and being sized to fit within the recess and a thermal barrier formed of porous material, which is interposed between opposing surfaces of the casing and the flange within the recess.
摘要翻译：提供一种隔热装置，其包括围绕涡轮机铲斗级并且从其内表面限定环形凹部的环形壳体，环形护罩，其设置在壳体内以提供关于涡轮机铲斗级的旋转铲斗前端的预定间隙所述护罩包括环形主构件和从所述主构件的面向外的表面延伸的环形凸缘，并且所述环形凸缘的尺寸被设计成适合于所述凹部内，并且由所述多孔材料形成的热屏障设置在所述壳体的相对表面之间，凹槽内的凸缘。

2. 发明授权

US09121301B2 Thermal isolation apparatus 有权
标题翻译：隔热装置
公开(公告)号：US09121301B2
公开(公告)日：2015-09-01
申请号：US13425029
申请日：2012-03-20
申请人： Donald Earl Floyd , David Martin Johnson
发明人： Donald Earl Floyd , David Martin Johnson
IPC分类号： F01D11/18 , F01D9/04
CPC分类号： F01D11/18 , F01D9/04 , F05D2300/502
摘要： A thermal isolation apparatus is provided and includes an annular casing surrounding a turbine bucket stage and defining an annular recess from an interior facing surface thereof, an annular shroud disposed within the casing to provide for a predefined clearance about rotating bucket tips of the turbine bucket stage, the shroud including an annular main member and an annular flange extending from an outwardly facing surface of the main member and being sized to fit within the recess and a thermal barrier formed of porous material, which is interposed between opposing surfaces of the casing and the flange within the recess.
摘要翻译：提供一种隔热装置，其包括围绕涡轮机铲斗级并且从其内表面限定环形凹部的环形壳体，环形护罩，其设置在壳体内以提供关于涡轮机铲斗级的旋转铲斗前端的预定间隙所述护罩包括环形主构件和从所述主构件的面向外的表面延伸的环形凸缘，并且所述环形凸缘的尺寸被设计成适合于所述凹部内，并且由所述多孔材料形成的热屏障设置在所述壳体的相对表面之间，凹槽内的凸缘。

3. 发明授权

US5906473A Removable inner turbine shell with bucket tip clearance control 失效
公开(公告)号：US5906473A
公开(公告)日：1999-05-25
申请号：US975358
申请日：1997-11-20
申请人： Brendan F. Sexton , Hans M. Knuijt , Sacheverel Q. Eldrid , Albert Myers , Kyle E. Coneybeer , David Martin Johnson , Iain R. Kellock
发明人： Brendan F. Sexton , Hans M. Knuijt , Sacheverel Q. Eldrid , Albert Myers , Kyle E. Coneybeer , David Martin Johnson , Iain R. Kellock
IPC分类号： F01D5/22 , F01D9/02 , F01D11/08 , F01D11/24 , F01D25/14 , F01D25/26 , F01D25/28 , F02C7/16 , F02C7/18 , F02C7/28
CPC分类号： F01D11/24 , F01D25/14 , F01D25/26 , F01D25/285 , F02C7/18 , F05D2230/642 , F05D2230/644 , F05D2230/70 , F05D2240/90 , F05D2260/205 , F05D2260/232 , F05D2260/2322
摘要： A turbine includes a plurality of inner shell sections mounting first and second stage nozzle and shroud portions. The inner shell sections are pinned to an outer containment shell formed of sections to preclude circumferential movement of the inner shell relative to the outer shell and enable thermal expansion and contraction of the inner shell relative to the outer shell. Positive bucket tip clearance control is afforded by passing a thermal medium about the inner shell in heat transfer relation with the shrouds about the first and second stage bucket tips, the thermal medium being provided from a source of heating/cooling fluid independent of the turbine. Access is provided to the rotor and turbine buckets by removing the outer and inner shell sections.

4. 发明授权

US08683804B2 Premixing apparatus for fuel injection in a turbine engine 有权
标题翻译：用于在涡轮发动机中燃料喷射的预混合装置
公开(公告)号：US08683804B2
公开(公告)日：2014-04-01
申请号：US12618636
申请日：2009-11-13
申请人： Gregory Allen Boardman , David Martin Johnson , Ronald James Chila , Nishant Govindbhai Parsania , Hasan Karim , Joseph Citeno
发明人： Gregory Allen Boardman , David Martin Johnson , Ronald James Chila , Nishant Govindbhai Parsania , Hasan Karim , Joseph Citeno
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/40 , F23C13/06 , F23R3/286
摘要： In one embodiment, a system includes a fuel nozzle that includes a fuel injector that includes a fuel port and a premixer tube. The premixer tube includes a wall disposed about a central passage, multiple air ports extending through the wall into the central passage, and a catalytic region. The catalytic region includes a catalyst, disposed inside the wall along the central passage, configured to increase a reaction of fuel and air.
摘要翻译：在一个实施例中，系统包括燃料喷嘴，其包括燃料喷射器，燃料喷射器包括燃料口和预混合管。预混合管包括围绕中心通道设置的壁，多个空气端口延伸穿过壁进入中心通道，以及催化区域。催化区域包括沿着中心通道设置在壁内的催化剂，构造成增加燃料和空气的反应。

5. 发明授权

US08540486B2 Apparatus for cooling a bucket assembly 有权
标题翻译：用于冷却铲斗组件的装置
公开(公告)号：US08540486B2
公开(公告)日：2013-09-24
申请号：US12728517
申请日：2010-03-22
申请人： David Martin Johnson
发明人： David Martin Johnson
IPC分类号： F01D5/08
CPC分类号： F01D5/186 , F01D5/12 , F01D5/18 , F01D5/181 , F01D5/22 , F01D5/24 , F01D5/26 , F01D5/30 , F01D11/006 , F01D25/12 , F05D2260/202
摘要： A bucket assembly cooling apparatus is provided. The bucket assembly includes a platform, an airfoil, and a shank. The airfoil may extend radially outward from the platform. The shank may extend radially inward from the platform. The shank may include a pressure side sidewall, a suction side sidewall, an upstream sidewall, and a downstream sidewall. The sidewalls may at least partially define a cooling circuit. The cooling circuit may be configured to receive a cooling medium and provide the cooling medium to the airfoil. The upstream sidewall may at least partially define an interior cooling passage and at least partially define an exterior ingestion zone. The cooling passage may be configured to provide a portion of the cooling medium from the cooling circuit to the ingestion zone of an adjacent bucket assembly.
摘要翻译：提供一种铲斗总成冷却装置。铲斗组件包括平台，翼型件和柄。翼型件可以从平台径向向外延伸。柄可以从平台径向向内延伸。柄部可以包括压力侧壁，吸力侧壁，上游侧壁和下游侧壁。侧壁可以至少部分地限定冷却回路。冷却回路可以被配置为接收冷却介质并将冷却介质提供给翼型件。上游侧壁可以至少部分地限定内部冷却通道并且至少部分限定外部摄取区域。冷却通道可以构造成将冷却介质的一部分从冷却回路提供给相邻铲斗组件的摄入区。

6. 发明申请

US20120227371A1 SYSTEM FOR COOLING AND PURGING EXHAUST SECTION OF GAS TURBINE ENGINE 有权
标题翻译：气体涡轮发动机冷却和清洗排气系统
公开(公告)号：US20120227371A1
公开(公告)日：2012-09-13
申请号：US13044491
申请日：2011-03-09
申请人： David Martin Johnson , Radu Ioan Danescu , Srinivasarao Pakkala , Piotr Edward Kobek
发明人： David Martin Johnson , Radu Ioan Danescu , Srinivasarao Pakkala , Piotr Edward Kobek
IPC分类号： F02C7/12
CPC分类号： F01D9/065 , F01D5/187 , F01D25/12 , F01D25/125 , F01D25/162 , F01D25/30 , F05D2260/205 , F05D2260/608 , Y02T50/676
摘要： A system is provided with a turbine exhaust strut configured to provide a bi-directional airflow. The turbine exhaust strut includes a first portion having a first flow passage configured to flow a fluid in a first direction between inner and outer exhaust walls of a turbine exhaust section, and a second portion having a second flow passage configured to flow the fluid in a second direction between the inner and outer exhaust walls of the turbine exhaust section. Furthermore, the first and second directions are opposite from one another.
摘要翻译：一个系统设置有被配置成提供双向气流的涡轮机排气支柱。涡轮机排气支柱包括具有第一流动通道的第一部分，第一流动通道构造成在涡轮机排气部分的内部排气壁和外部排气壁之间沿第一方向流动流体，第二部分具有第二流动通道，其被配置为使流体在在涡轮机排气部分的内排气壁和外排气壁之间的第二方向。此外，第一和第二方向彼此相反。

7. 发明申请

US20120045337A1 TURBINE BUCKET ASSEMBLY AND METHODS FOR ASSEMBLING SAME 审中-公开
标题翻译：涡轮泵组件及其装配方法
公开(公告)号：US20120045337A1
公开(公告)日：2012-02-23
申请号：US12860493
申请日：2010-08-20
申请人： Michael James Fedor , David Martin Johnson
发明人： Michael James Fedor , David Martin Johnson
IPC分类号： F01D11/00 , F01D5/30 , B21K25/00
CPC分类号： F01D11/006 , Y10T29/49321
摘要： A method for assembling a rotor assembly for use with a turbine engine. The method includes providing at least two rotor blades that each include a shank extending between a dovetail and a platform. The shank includes at least one cover plate that extends inwardly from the platform towards the dovetail. An airfoil extends outwardly from the platform. A first rotor blade is coupled to a rotor disk. A second rotor blade is coupled to the rotor disk, such that a cavity is defined between the first and second rotor blades, and such that a seal path is defined between a first rotor blade cover plate and a second rotor blade cover plate.
摘要翻译：一种用于组装与涡轮发动机一起使用的转子组件的方法。该方法包括提供至少两个转子叶片，每个转子叶片包括在燕尾榫和平台之间延伸的柄部。柄部包括至少一个从平台朝向燕尾榫向内延伸的盖板。机翼从平台向外延伸。第一转子叶片联接到转子盘。第二转子叶片联接到转子盘，使得在第一和第二转子叶片之间限定空腔，并且使得密封路径被限定在第一转子叶片盖板和第二转子叶片盖板之间。

8. 发明申请

US20100132364A1 FUEL NOZZLE DETACHABLE BURNER TUBE 有权
标题翻译：燃油喷嘴可拆卸燃烧器管
公开(公告)号：US20100132364A1
公开(公告)日：2010-06-03
申请号：US12325559
申请日：2008-12-01
申请人： Geoffrey D. Myers , Scott Simmons , Stephen R. Thomas , Donald Mark Bailey , David Martin Johnson
发明人： Geoffrey D. Myers , Scott Simmons , Stephen R. Thomas , Donald Mark Bailey , David Martin Johnson
IPC分类号： F02C1/00 , B21D39/00
CPC分类号： F23R3/283 , F23R2900/00017 , Y10T29/49826
摘要： A fuel nozzle for use with a combustion chamber defined within a gas turbine engine and a method for assembling the same are provided. The fuel nozzle includes a swirler assembly and a burner tube that is coupled to a support flange in a detachable manner such that an inner surface of the burner tube circumscribes an outer surface of the swirler assembly during fuel nozzle operation.
摘要翻译：提供了一种与燃气涡轮发动机内限定的燃烧室一起使用的燃料喷嘴及其组装方法。燃料喷嘴包括旋流器组件和燃烧器管，其以可拆卸的方式联接到支撑凸缘，使得在燃料喷嘴操作期间燃烧器管的内表面围绕旋流器组件的外表面。

9. 发明授权

US07571611B2 Methods and system for reducing pressure losses in gas turbine engines 有权
标题翻译：减少燃气轮机发动机压力损失的方法和系统
公开(公告)号：US07571611B2
公开(公告)日：2009-08-11
申请号：US11409807
申请日：2006-04-24
申请人： David Martin Johnson , Kenneth Neil Whaling , Ronald Scott Bunker
发明人： David Martin Johnson , Kenneth Neil Whaling , Ronald Scott Bunker
IPC分类号： F23R3/00
CPC分类号： F23R3/005 , F01D9/023 , F01D25/14 , F23R3/04 , F23R2900/03044
摘要： A method of assembling a combustor assembly is provided, wherein the method includes providing a combustor liner having a centerline axis and defining a combustion chamber therein, and coupling an annular flowsleeve radially outward from the combustor liner such that an annular flow path is defined substantially circumferentially between the flowsleeve and the combustor liner. The method also includes orienting the flowsleeve such that a plurality of inlets formed within the flowsleeve are positioned to inject cooling air in a substantially axial direction into the annular flow path to facilitate cooling the combustor liner.
摘要翻译：提供了一种组装燃烧器组件的方法，其中所述方法包括提供具有中心线轴线并且在其中限定燃烧室的燃烧器衬套，并且将环形流动叶片从燃烧器衬套径向向外耦合，使得环形流动路径基本上周向地限定在流动与燃烧器衬套之间。该方法还包括使流动方向定向，使得形成在流动中的多个入口被定位成将大致轴向的冷却空气注入到环形流动路径中以便于冷却燃烧器衬套。

10. 发明授权

US08979477B2 System for cooling and purging exhaust section of gas turbine engine 有权
标题翻译：燃气轮机发动机排气段冷却排气系统
公开(公告)号：US08979477B2
公开(公告)日：2015-03-17
申请号：US13044491
申请日：2011-03-09
申请人： David Martin Johnson , Radu Ioan Danescu , Srinivasarao Pakkala , Piotr Edward Kobek
发明人： David Martin Johnson , Radu Ioan Danescu , Srinivasarao Pakkala , Piotr Edward Kobek
IPC分类号： F01D9/06 , F01D25/16 , F01D25/30
CPC分类号： F01D9/065 , F01D5/187 , F01D25/12 , F01D25/125 , F01D25/162 , F01D25/30 , F05D2260/205 , F05D2260/608 , Y02T50/676
摘要： A system is provided with a turbine exhaust strut configured to provide a bi-directional airflow. The turbine exhaust strut includes a first portion having a first flow passage configured to flow a fluid in a first direction between inner and outer exhaust walls of a turbine exhaust section, and a second portion having a second flow passage configured to flow the fluid in a second direction between the inner and outer exhaust walls of the turbine exhaust section. Furthermore, the first and second directions are opposite from one another.
摘要翻译：一个系统设置有被配置成提供双向气流的涡轮机排气支柱。涡轮机排气支柱包括具有第一流动通道的第一部分，第一流动通道构造成在涡轮机排气部分的内部排气壁和外部排气壁之间沿第一方向流动流体，第二部分具有第二流动通道，其被配置为使流体在在涡轮机排气部分的内排气壁和外排气壁之间的第二方向。此外，第一和第二方向彼此相反。

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