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1. 发明申请

US20090145137A1 TRANSITION DUCT ASSEMBLY 有权
标题翻译：过渡式大楼
公开(公告)号：US20090145137A1
公开(公告)日：2009-06-11
申请号：US12196629
申请日：2008-08-22
申请人： Hany Rizkalla , Stephen W. Jorgensen , Peter Stuttaford , Plazi Ricklin , David John Henriquez
发明人： Hany Rizkalla , Stephen W. Jorgensen , Peter Stuttaford , Plazi Ricklin , David John Henriquez
IPC分类号： F02C7/00
CPC分类号： F01D9/023 , F01D25/28 , F05D2230/642 , F05D2260/96
摘要： A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.
摘要翻译：公开了一种具有无热的后框架和用于燃气涡轮发动机的安装系统的过渡管道组件。后框架能够调节到热梯度，而安装系统在发动机组装期间至少提供过渡管道的横向移动。安装系统还提供了一种用于提高过渡管道在发动机动态励磁范围之外的固有频率的装置。

2. 发明授权

US08322146B2 Transition duct assembly 有权
标题翻译：过渡管总成
公开(公告)号：US08322146B2
公开(公告)日：2012-12-04
申请号：US12196629
申请日：2008-08-22
申请人： Hany Rizkalla , Stephen W. Jorgensen , Peter Stuttaford , Plazi Ricklin , David John Henriquez
发明人： Hany Rizkalla , Stephen W. Jorgensen , Peter Stuttaford , Plazi Ricklin , David John Henriquez
IPC分类号： F02C7/20 , F02C1/00 , F02G3/00
CPC分类号： F01D9/023 , F01D25/28 , F05D2230/642 , F05D2260/96
摘要： A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.
摘要翻译：公开了一种具有无热的后框架和用于燃气涡轮发动机的安装系统的过渡管道组件。后框架能够调节到热梯度，而安装系统在发动机组装期间至少提供过渡管道的横向移动。安装系统还提供了一种用于提高过渡管道在发动机动态励磁范围之外的固有频率的装置。

3. 发明授权

US08418474B2 Altering a natural frequency of a gas turbine transition duct 有权
标题翻译：改变燃气轮机过渡管的固有频率
公开(公告)号：US08418474B2
公开(公告)日：2013-04-16
申请号：US12240380
申请日：2008-09-29
申请人： Hany Rizkalla , Stephen W. Jorgensen , Peter Stuttaford
发明人： Hany Rizkalla , Stephen W. Jorgensen , Peter Stuttaford
IPC分类号： F02C7/20 , F02C1/00 , F02G3/00
CPC分类号： F01D9/023 , F05D2260/96
摘要： A transition duct having a thermally free aft frame and being capable of adjusting the natural frequency is disclosed. The aft frame is capable of permitting movement due to thermal gradients with the transition duct. The transition duct utilizes a spring plate located adjacent to an aft mounting bracket, where the spring plate, based on its thickness can either increase or decrease a frequency of the transition duct. Such an arrangement ensures that the transition duct natural frequency does not coincide with or cross other critical engine and/or combustor frequencies.
摘要翻译：公开了一种具有热释放后框架并且能够调节固有频率的过渡管道。后框架能够由于过渡管道的热梯度而允许移动。过渡管道使用位于后部安装支架附近的弹簧板，其中弹簧板基于其厚度可以增加或减小过渡管道的频率。这种布置确保了过渡管道固有频率不与其它关键的发动机和/或燃烧器频率重合或交叉。

4. 发明申请

US20090188258A1 ALTERING A NATURAL FREQUENCY OF A GAS TURBINE TRANSITION DUCT 有权
标题翻译：改变气体涡轮转换管道的自然频率
公开(公告)号：US20090188258A1
公开(公告)日：2009-07-30
申请号：US12240380
申请日：2008-09-29
申请人： Hany Rizkalla , Stephen W. Jorgensen , Peter Stuttaford
发明人： Hany Rizkalla , Stephen W. Jorgensen , Peter Stuttaford
IPC分类号： F02C7/20
CPC分类号： F01D9/023 , F05D2260/96
摘要： A transition duct having a thermally free aft frame and being capable of adjusting the natural frequency is disclosed. The aft frame is capable of permitting movement due to thermal gradients with the transition duct. The transition duct utilizes a spring plate located adjacent to an aft mounting bracket, where the spring plate, based on its thickness can either increase or decrease a frequency of the transition duct. Such an arrangement ensures that the transition duct natural frequency does not coincide with or cross other critical engine and/or combustor frequencies.
摘要翻译：公开了一种具有热释放后框架并且能够调节固有频率的过渡管道。后框架能够由于过渡管道的热梯度而允许移动。过渡管道使用位于后部安装支架附近的弹簧板，其中弹簧板基于其厚度可以增加或减小过渡管道的频率。这种布置确保了过渡管道固有频率不与其它关键的发动机和/或燃烧器频率重合或交叉。

5. 发明授权

US08151570B2 Transition duct cooling feed tubes 有权
标题翻译：过渡管冷却进料管
公开(公告)号：US08151570B2
公开(公告)日：2012-04-10
申请号：US11951790
申请日：2007-12-06
申请人： Stephen Jennings , Peter Stuttaford , Stephen W. Jorgensen
发明人： Stephen Jennings , Peter Stuttaford , Stephen W. Jorgensen
IPC分类号： F02C1/00
CPC分类号： F01D25/12 , F01D9/023 , F05D2260/20 , F05D2260/201
摘要： Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct.
摘要翻译：公开了用于向燃气轮机过渡管道提供冷却流体以降低过渡管道的有效操作温度的装置和相关方法的实施例。过渡管道具有内衬和径向向外定位的冲击套筒，其间形成有通道。冲击套筒具有多个开口，其中开口的一部分各自具有延伸穿过开口并进入通道的进料管。进料管相对于冲击套筒定向成一定角度，使得进料管的入口通常朝着迎面而来的冷却流体流动。进料管将一部分冷却流体引向内衬并进入通道以冷却过渡管道。

6. 发明申请

US20090145099A1 TRANSITION DUCT COOLING FEED TUBES 有权
标题翻译： TRANSITION DUCT冷却进料管
公开(公告)号：US20090145099A1
公开(公告)日：2009-06-11
申请号：US11951790
申请日：2007-12-06
申请人： Stephen Jennings , Peter Stuttaford , Stephen W. Jorgensen
发明人： Stephen Jennings , Peter Stuttaford , Stephen W. Jorgensen
IPC分类号： F01D25/12 , F02C3/00 , F02C7/12
CPC分类号： F01D25/12 , F01D9/023 , F05D2260/20 , F05D2260/201
摘要： Embodiments for an apparatus and associated method for providing a cooling fluid to a gas turbine transition duct in order to lower the effective operating temperatures of the transition duct are disclosed. The transition duct has an inner liner and an impingement sleeve positioned radially outward with a passageway formed therebetween. The impingement sleeve has a plurality of openings where a portion of the openings each have a feed tube extending through the opening and into the passageway. The feed tubes are oriented at an angle relative to the impingement sleeve, such that an inlet to the feed tube is directed generally towards an oncoming flow of cooling fluid. The feed tubes direct a portion of the cooling fluid toward the inner liner and into the passageway for cooling of the transition duct.
摘要翻译：公开了用于向燃气轮机过渡管道提供冷却流体以降低过渡管道的有效操作温度的装置和相关方法的实施例。过渡管道具有内衬和径向向外定位的冲击套筒，其间形成有通道。冲击套筒具有多个开口，其中开口的一部分各自具有延伸穿过开口并进入通道的进料管。进料管相对于冲击套筒定向成一定角度，使得进料管的入口通常朝着迎面而来的冷却流体流动。进料管将一部分冷却流体引向内衬并进入通道以冷却过渡管道。

7. 发明申请

US20170003032A1 GAS TURBINE CONTROL SYSTEM 审中-公开
标题翻译：气体涡轮控制系统
公开(公告)号：US20170003032A1
公开(公告)日：2017-01-05
申请号：US15194213
申请日：2016-06-27
申请人： Stephen W. Jorgensen , Joshua R. McNally , Douglas Pennell , Donald Gauthier , Pawel Matys , Marc Paskin , Thomas R. Ruck , Peter John Stuttaford , Bernard Tam-Yen Sam
发明人： Stephen W. Jorgensen , Joshua R. McNally , Douglas Pennell , Donald Gauthier , Pawel Matys , Marc Paskin , Thomas R. Ruck , Peter John Stuttaford , Bernard Tam-Yen Sam
IPC分类号： F23R3/34 , F23R3/28 , F23R3/36 , F23R3/00 , F23R3/14
CPC分类号： F23R3/346 , F02C7/222 , F02C7/232 , F05D2220/32 , F05D2230/237 , F05D2260/14 , F05D2260/30 , F05D2260/99 , F23R3/002 , F23R3/14 , F23R3/20 , F23R3/283 , F23R3/286 , F23R3/343 , F23R3/36 , F23R3/44 , F23R3/54
摘要： Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary combustor and/or fuel cartridge assembly may comprise first and second fuel circuits or manifolds. Methods and systems are also provided for staging and controlling a flow of fuel and/or water through different fuel circuits and pilot injectors, to allow purging and ignition using different fuel circuits, pilot injectors, and fuel sources.
摘要翻译：提供燃气轮机燃烧系统和燃料盒组件。示例性燃烧系统可以包括燃烧器，该燃烧器包括圆柱形燃烧衬套，流动套筒，主混合器，径向流入旋流器，燃烧器圆顶和燃料盒组件。示例性燃烧器和/或燃料盒组件可以包括第一和第二燃料回路或歧管。还提供了方法和系统，用于通过不同的燃料回路和先导喷射器分级和控制燃料和/或水的流动，以允许使用不同的燃料回路，引燃喷射器和燃料源进行清洗和点火。

8. 发明申请

US20170002742A1 FUEL INJECTION LOCATIONS BASED ON COMBUSTOR FLOW PATH 审中-公开
标题翻译：燃油喷射位置基于COMBUSTOR流程
公开(公告)号：US20170002742A1
公开(公告)日：2017-01-05
申请号：US15194203
申请日：2016-06-27
申请人： Stephen W. Jorgensen , Joshua R. McNally , Douglas Pennell , Donald Gauthier , Pawel Matys , Marc Paskin , Thomas R. Ruck , Peter John Stuttaford , Bernard Tam-Yen Sam
发明人： Stephen W. Jorgensen , Joshua R. McNally , Douglas Pennell , Donald Gauthier , Pawel Matys , Marc Paskin , Thomas R. Ruck , Peter John Stuttaford , Bernard Tam-Yen Sam
IPC分类号： F02C7/22 , F23R3/28 , F23R3/36 , F23R3/00
摘要： Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly, one or more of which may be configured to supply either a gaseous or a liquid fuel to the combustion liner, depending on whether gaseous fuel operation or liquid fuel operation of the combustor is desired.
摘要翻译：提供了一种用于燃气轮机燃烧器的双燃料操作的系统和方法。示例性的燃气轮机燃烧器可以包括一个或多个部件，例如圆柱形燃烧衬套，流动套筒，主混合器，径向流入旋流器，燃烧器圆顶和燃料盒组件，其中一个或多个可以被配置根据气体燃料操作或燃烧器的液体燃料操作是否需要，向燃烧衬套供应气体或液体燃料。

9. 发明授权

US06675584B1 Coated seal article used in turbine engines 失效
标题翻译：用于涡轮发动机的涂层密封件
公开(公告)号：US06675584B1
公开(公告)日：2004-01-13
申请号：US10064768
申请日：2002-08-15
申请人： Terry L. Hollis , Gerry A. Sileo , Stephen W. Jorgensen , Robert J. Kraft , Vincent C. Martling
发明人： Terry L. Hollis , Gerry A. Sileo , Stephen W. Jorgensen , Robert J. Kraft , Vincent C. Martling
IPC分类号： F02C720
CPC分类号： F01D11/005 , F01D9/023 , F02C7/20 , F05D2240/55 , F16J15/0806 , F16J15/0887
摘要： An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform.
摘要翻译：公开了一种用于过渡管道后部框架和涡轮机入口之间的改进的密封装置。改进的密封装置包括多个波纹金属密封件，其沿着后框架的弧形部分固定到过渡管道后部框架。波纹密封件接触过渡管道后部框架和涡轮机入口以提供更有效的密封并且控制引入以冷却涡轮叶片平台的压缩机排出空气的量。在优选实施例中，波纹状密封件被涂覆以减少磨损，磨损和磨损，并且与过渡管道热释放后框架和枢转轴承安装系统结合使用。还公开了密封件的替代实施例，其利用替代的冷却孔图案来向涡轮叶片平台提供额外的冷却空气。

10. 发明授权

US4878811A Axial compressor blade assembly 失效
标题翻译：轴向压缩机叶片总成
公开(公告)号：US4878811A
公开(公告)日：1989-11-07
申请号：US270994
申请日：1988-11-14
申请人： Stephen W. Jorgensen
发明人： Stephen W. Jorgensen
IPC分类号： F04D29/34 , F01D5/30 , F01D11/00
CPC分类号： F01D11/006
摘要： Blade platforms (26) for compressor blades with airfoils (22) in high solidity relationship have edges of a major portion (44) a minor portion (46), and a canted intermediate portion (48). Minimum clearance (54) exists between the major portions (44) whereby twisting during stackup or operation is avoided. A circumferential seal (60, 64) is located under the platform coincident with major portion (44).

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