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1. 发明申请

US20170002743A1 GAS TURBINE FUEL COMPONENTS 审中-公开
标题翻译：燃气涡轮机燃油部件
公开(公告)号：US20170002743A1
公开(公告)日：2017-01-05
申请号：US15194209
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 , F23R3/34 , F23R3/28 , F02C7/232 , F23R3/00
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 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. An exemplary fuel cartridge assembly may comprise first and second fuel manifolds which are connected to respective fuel circuits which supply fuel, such as liquid fuel, through a plurality of fuel passages within the fuel cartridge assembly or to other locations within an associated combustor. The fuel cartridge assembly may further include a plurality of fuel injector tips located at a tip plate of the fuel cartridge assembly through which fuel may be supplied to an associated combustor.
摘要翻译：提供燃气轮机燃烧系统和燃料盒组件。示例性燃烧系统可包括包括一个或多个部件的燃烧器，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。示例性的燃料盒组件可以包括第一和第二燃料歧管，其连接到通过燃料盒组件内的多个燃料通道或相关燃烧器内的其它位置供应诸如液体燃料的燃料的各个燃料回路。燃料盒组件还可以包括位于燃料盒组件的顶板处的多个燃料喷射器尖端，燃料可以通过燃料喷射器提供给相关联的燃烧器。

2. 发明授权

US09328669B2 Dynamic and automatic tuning of a gas turbine engine using exhaust temperature and inlet guide vane angle 有权
标题翻译：使用排气温度和入口导叶角度对燃气涡轮发动机进行动态和自动调谐
公开(公告)号：US09328669B2
公开(公告)日：2016-05-03
申请号：US14213263
申请日：2014-03-14
申请人： Hany Rizkalla , Donald Gauthier , Peter John Stuttaford , Sumit Soni
发明人： Hany Rizkalla , Donald Gauthier , Peter John Stuttaford , Sumit Soni
IPC分类号： F02C9/22 , G05B15/02 , F02C9/00 , F02C9/48
CPC分类号： F02C9/22 , F02C9/00 , F02C9/48 , F05D2260/964 , G05B15/02
摘要： Methods and systems are provided for dynamically auto-tuning a gas turbine engine. Initially, parameters of the gas turbine engine are monitored to determine that they are within predefined upper and lower limits such that a margin exists. A first incremental adjustment of an inlet guide vane (IGV) angle is performed. If the monitored parameters are still within the predefined upper and lower limits, a second incremental adjustment of the IGV angle is performed. It is determined that the monitored parameters are still within the predefined upper and lower limits. Additionally, it is determined that a predefined value of the IGV angle has been reached such that the IGV angle is not to be further increased or decreased.
摘要翻译：提供了用于动态自动调节燃气涡轮发动机的方法和系统。首先，监测燃气涡轮发动机的参数以确定它们在预定义的上限和下限内，使得存在余量。执行入口导叶（IGV）角度的第一增量调节。如果监视的参数仍处于预定义的上限和下限范围内，则执行IGV角度的第二增量调整。确定监控的参数仍然在预定义的上限和下限之内。此外，确定已经达到了IGV角度的预定值，使得IGV角度不被进一步增加或减小。

3. 发明申请

US20140090396A1 COMBUSTOR WITH RADIALLY STAGED PREMIXED PILOT FOR IMPROVED 审中-公开
标题翻译：具有放射性标记的预先引导的COMBUSTOR改进
公开(公告)号：US20140090396A1
公开(公告)日：2014-04-03
申请号：US14038029
申请日：2013-09-26
申请人： PETER JOHN STUTTAFORD , STEPHEN JORGENSEN , YAN CHEN , HANY RIZKALLA , KHALID OUMEJJOUD , JEREMY METTERNICH
发明人： PETER JOHN STUTTAFORD , STEPHEN JORGENSEN , YAN CHEN , HANY RIZKALLA , KHALID OUMEJJOUD , JEREMY METTERNICH
IPC分类号： F23R3/28
CPC分类号： F23R3/54 , F23C2201/20 , F23C2900/06043 , F23C2900/07001 , F23R3/14 , F23R3/16 , F23R3/26 , F23R3/286 , F23R3/34 , F23R3/343 , F23R3/60 , F23R2900/00014 , F23R2900/03343
摘要： The present invention discloses a novel apparatus and method for a mixing fuel and air in a gas turbine combustion system. The mixer helps to mix fuel and air while being able to selectively increase the fuel flow to a shear to a shear layer of a pilot flame in order to reduce polluting emissions. The mixer directs a flow of air radially inward into the combustion system and includes two sets of fuel injectors within each radially-oriented vane. A first plurality of fuel injectors operate independent of a second plurality of fuel injectors and the second plurality of fuel injectors are positioned to selectively modulate the fuel flow to the shear layer of the resulting pilot flame.
摘要翻译：本发明公开了一种在燃气轮机燃烧系统中混合燃料和空气的新型装置和方法。混合器有助于混合燃料和空气，同时能够选择性地增加燃料流到导向火焰剪切层的剪切以减少污染排放。混合器将空气流径向向内引导到燃烧系统中，并且在每个径向定向的叶片内包括两组燃料喷射器。第一多个燃料喷射器独立于第二多个燃料喷射器操作，并且第二多个燃料喷射器被定位成选择性地调节到所得到的导向火焰的剪切层的燃料流。

4. 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。

5. 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。

6. 发明申请

US20090293444A1 GAS TURBINE INTEGRATED WITH FUEL CATALYTIC PARTIAL OXIDATION 有权
标题翻译：燃料气体与燃料催化部分氧化
公开(公告)号：US20090293444A1
公开(公告)日：2009-12-03
申请号：US12131252
申请日：2008-06-02
申请人： PETER JOHN STUTTAFORD
发明人： PETER JOHN STUTTAFORD
IPC分类号： F02B43/00
CPC分类号： F02C3/28 , F02C3/20 , F05D2240/36 , Y02E20/16
摘要： A system and method for removing at least carbon from a fuel/air mixture prior to injection of the fuel/air mixture into a combustion system is disclosed. The system fully integrates the combined cycle power plant with carbon scrubbing of the fuel/air mixture to increase overall cycle efficiency while capturing carbon from the cycle. A portion of the compressed air source generated by the gas turbine compressor is provided to a premixer where it is mixed with a natural gas to form a fuel/air mixture. The fuel/air mixture passes through a catalytic partial oxidation (CPOX) reactor, which utilizes a precious metal to partially oxidize the hydrocarbons into carbon monoxide. The mixture passes through a shift reactor to complete generation of carbon dioxide and raise hydrogen yield of the fuel/air mixture. Carbon constituents are then removed from the mixture by a separator.
摘要翻译：公开了一种用于在将燃料/空气混合物注入燃烧系统之前从燃料/空气混合物中去除至少碳的系统和方法。该系统将联合循环发电厂与燃料/空气混合物的碳清洗完全整合，以提高整体循环效率，同时从循环中捕获碳。由燃气涡轮压缩机产生的压缩空气源的一部分被提供给预混合器，在该预混合器中与天然气混合以形成燃料/空气混合物。燃料/空气混合物通过催化部分氧化（CPOX）反应器，其利用贵金属将烃部分氧化成一氧化碳。混合物通过变换反应器以完成二氧化碳的产生并提高燃料/空气混合物的氢产率。然后通过分离器从混合物中除去碳成分。

7. 发明授权

US06745571B2 Method of combustor cycle airflow adjustment 有权
标题翻译：燃烧器循环气流调节方法
公开(公告)号：US06745571B2
公开(公告)日：2004-06-08
申请号：US10421751
申请日：2003-04-24
申请人： Peter John Stuttaford , Aleksandar Kojovic
发明人： Peter John Stuttaford , Aleksandar Kojovic
IPC分类号： F23R306
CPC分类号： F23R3/005 , F02C7/08 , F05D2260/201 , F23R3/26 , F23R2900/00016 , F23R2900/03044
摘要： A method of combustor cycle air flow adjustment for a gas turbine engine according to the present invention solves the problem of a higher flame temperature in the combustor, thereby affecting the emission levels when a heat-recuperated air flow cycle is used to increase the compressed air temperature. In low emission combustors this impact is severe because emission levels are significantly dependent on the primary combustion zone flame temperature. The method of the present invention includes a step of changing a geometry of an air flow passage and thereby changing distribution of a total air mass flow between an air mass flow for combustion and an air mass flow for cooling in order to ensure that flame temperature in a primary combustion zone of a combustor are maintained substantially the same whether the gas turbine engine is manufactured to operate as a simple air flow cycle engine or as a heat-recuperated air flow cycle engine. In an embodiment of the present invention, the changing of the geometry of the air flow passage by changing the number and size of perforations in an impingement cooling skin so that with minimal changes the impingement cooling skin serves duel purposes both as a cooling device for cooling the combustor wall and as a valve means for combustor cycle air flow adjustment, which makes the method simple and economical.
摘要翻译：根据本发明的用于燃气涡轮发动机的燃烧器循环空气流量调节方法解决了燃烧器中火焰温度较高的问题，从而当使用热回收空气流循环来增加压缩空气时影响排放水平温度。在低排放燃烧器中，这种影响是严重的，因为排放水平显着取决于主燃烧区火焰温度。本发明的方法包括改变空气流路的几何形状，从而改变用于燃烧的空气质量流与冷却空气质量流之间的总空气质量流的分布，以确保火焰温度在无论燃气涡轮发动机是否被制造成作为简单的气流循环发动机或作为热回收空气流循环发动机来操作，燃烧器的主燃烧区域保持基本相同。在本发明的一个实施例中，通过改变冲击冷却皮肤中的穿孔的数量和尺寸来改变空气流动通道的几何形状，使得在最小变化的情况下，冲击冷却皮肤作为用于冷却的冷却装置的决斗燃烧器壁和用于燃烧器循环空气流量调节的阀装置，这使得该方法简单和经济。

8. 发明申请

US20160084169A1 METHOD OF OPERATING A MULTI-STAGE FLAMESHEET COMBUSTOR 审中-公开
标题翻译：操作多级火焰喷墨打印机的方法
公开(公告)号：US20160084169A1
公开(公告)日：2016-03-24
申请号：US14956048
申请日：2015-12-01
申请人： Peter John Stuttaford , Stephen Jorgensen , Yan Chen , Hany Rizkalla , Khalid Oumejjoud , Nicolas Demougeot
发明人： Peter John Stuttaford , Stephen Jorgensen , Yan Chen , Hany Rizkalla , Khalid Oumejjoud , Nicolas Demougeot
IPC分类号： F02C9/28 , F23R3/34
CPC分类号： F02C9/28 , F02C7/228 , F02C9/26 , F02C9/34 , F05D2270/08 , F05D2270/082 , F05D2270/091 , F05D2270/303 , F05D2270/304 , F05D2270/31 , F05D2270/331 , F05D2270/335 , F23R3/286 , F23R3/343 , F23R3/346 , F23R2900/03343
摘要： The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide, are kept within acceptable levels.
摘要翻译：本发明公开了一种使用检测温度和检测到的涡轮转子速度来控制燃气涡轮发动机的新方法。操作系统为燃气轮机燃烧器提供了一系列操作模式，通过燃料涡轮机燃烧器分级燃料以逐渐增加发动机功率，但有害的排放物（例如一氧化碳）保持在可接受的水平内。

9. 发明申请

US20150184858A1 METHOD OF OPERATING A MULTI-STAGE FLAMESHEET COMBUSTOR 审中-公开
标题翻译：操作多级火焰喷墨打印机的方法
公开(公告)号：US20150184858A1
公开(公告)日：2015-07-02
申请号：US14038070
申请日：2013-09-26
申请人： PETER JOHN STUTTAFORD , STEPHEN JORGENSEN , YAN CHEN , HANY RIZKALLA , KHALID OUMEJJOUD , NICOLAS DEMOUGEOT
发明人： PETER JOHN STUTTAFORD , STEPHEN JORGENSEN , YAN CHEN , HANY RIZKALLA , KHALID OUMEJJOUD , NICOLAS DEMOUGEOT
IPC分类号： F23R3/34
CPC分类号： F23R3/346 , F02C9/26 , F05D2270/08 , F05D2270/082 , F05D2270/091 , F05D2270/331 , F05D2270/335 , F23R3/286 , F23R3/343 , F23R2900/03343
摘要： The present invention discloses a novel way of controlling a gas turbine engine to reduce emissions levels when demand for power from the gas turbine engine is reduced. The operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide are kept within acceptable levels.
摘要翻译：本发明公开了一种当从燃气涡轮发动机的动力需求减少时控制燃气涡轮发动机以减少排放水平的新方式。操作系统为燃气轮机燃烧器提供了一系列操作模式，通过燃料涡轮机燃烧器分级燃料逐渐增加发动机功率，但有害排放物（如一氧化碳）保持在可接受的水平。

10. 发明申请

US20150075172A1 FLAMESHEET COMBUSTOR CONTOURED LINER 审中-公开
标题翻译：火焰喷枪轮廓线
公开(公告)号：US20150075172A1
公开(公告)日：2015-03-19
申请号：US14549922
申请日：2014-11-21
申请人： PETER JOHN STUTTAFORD , HANY RIZKALLA
发明人： PETER JOHN STUTTAFORD , HANY RIZKALLA
IPC分类号： F23R3/54
CPC分类号： F23R3/54 , F23C2201/20 , F23C2900/06043 , F23C2900/07001 , F23R3/14 , F23R3/16 , F23R3/286 , F23R3/34 , F23R3/343 , F23R2900/00014 , F23R2900/03343
摘要： The present invention discloses a novel apparatus and way for reducing the recirculation zone at the inlet end of a combustor. The recirculation zone is reduced by altering the geometry of the inlet end through a tapering of the liner wall thickness and a tapering of the thermal barrier coating to reduce the bluff body effect at the combustion liner inlet end.
摘要翻译：本发明公开了一种用于减少燃烧器入口端的再循环区域的新型装置和方法。通过改变衬套壁厚度的锥形和隔热涂层的锥形，通过改变入口端的几何形状来减少再循环区域，以减少燃烧衬套入口端处的非流线体效应。

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