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1. 发明授权

US06804946B2 Combustion system with shutdown fuel purge 有权
标题翻译：燃油系统关闭燃油
公开(公告)号：US06804946B2
公开(公告)日：2004-10-19
申请号：US10720145
申请日：2003-11-25
申请人： Jeffrey W. Willis , Guillermo Pont , Edward C. Edelman , Gunther Linzner
发明人： Jeffrey W. Willis , Guillermo Pont , Edward C. Edelman , Gunther Linzner
IPC分类号： F02C7232
CPC分类号： F02C7/232 , F01D21/06 , F02C7/22 , F02C9/26 , F05D2260/602
摘要： Upon shutdown of a liquid fuel turbine engine, the liquid fuel supply is turned off and compressed air is passed through the fuel lines and fuel injectors to purge all remaining liquid fuel into the combustion chamber to be combusted therein.
摘要翻译：在关闭液体燃料涡轮发动机时，液体燃料供应被关闭，并且压缩空气通过燃料管线和燃料喷射器以将所有剩余的液体燃料吹扫到燃烧室中以在其中燃烧。

2. 发明授权

US06675583B2 Combustion method 有权
标题翻译：燃烧法
公开(公告)号：US06675583B2
公开(公告)日：2004-01-13
申请号：US09969491
申请日：2001-10-02
申请人： Jeffrey W. Willis , Guillermo Pont , Edward C. Edelman , Gunther Linzner
发明人： Jeffrey W. Willis , Guillermo Pont , Edward C. Edelman , Gunther Linzner
IPC分类号： F02C7232
CPC分类号： F02C7/232 , F01D21/06 , F02C7/22 , F02C9/26 , F05D2260/602
摘要： Upon shutdown of a liquid fuel turbine engine, the liquid fuel supply is turned off and compressed air is passed through the fuel lines and fuel injectors to purge all remaining liquid fuel into the combustion chamber to be combusted therein.
摘要翻译：在关闭液体燃料涡轮发动机时，液体燃料供应被关闭，并且压缩空气通过燃料管线和燃料喷射器以将所有剩余的液体燃料吹扫到燃烧室中以在其中燃烧。

3. 发明授权

US06405522B1 System and method for modular control of a multi-fuel low emissions turbogenerator 失效
公开(公告)号：US06405522B1
公开(公告)日：2002-06-18
申请号：US09453825
申请日：1999-12-01
申请人： Guillermo Pont , James Brian Dickey , Ed Edelman , Mark G. Gilbreth , Jeffrey W. Willis
发明人： Guillermo Pont , James Brian Dickey , Ed Edelman , Mark G. Gilbreth , Jeffrey W. Willis
IPC分类号： F02G726
CPC分类号： F02C9/28
摘要： A system and method for modular control of a multi-fuel turbogenerator include separate controllers for controlling fuel supplied to the combustor and power output from the generator. The power controller generates a fuel command based on the required turbine exhaust temperature, where the fuel command is independent of the particular fuel being used. Fuels may include natural gas, diesel, propane, waste gas, or gasoline, for example. The power controller communicates the fuel command and the airflow or calculated air/fuel ratio to the fuel controller which selects an appropriate mode of operation for the injectors. Injector operating modes include one or more pilot modes where fuel is not mixed with air prior to combustion, and one or more premix modes where fuel is highly mixed with air prior to combustion. The fuel controller implements closed-loop feedback control of a fuel metering device and controls the fuel injectors in the appropriate operating mode based on the fuel command, the energy content of the fuel being used, and the air/fuel ratio.

4. 发明授权

US06438937B1 System and method for modular control of a multi-fuel low emissions turbogenerator 有权
标题翻译：多燃料低排放涡轮发电机的模块化控制系统和方法
公开(公告)号：US06438937B1
公开(公告)日：2002-08-27
申请号：US09972672
申请日：2001-10-05
申请人： Guillermo Pont , James Brian Dickey , Ed Edelman , Mark G. Gilbreth , Jeffrey W. Willis
发明人： Guillermo Pont , James Brian Dickey , Ed Edelman , Mark G. Gilbreth , Jeffrey W. Willis
IPC分类号： F02G726
CPC分类号： F02C9/28
摘要： A system and method for modular control of a multi-fuel turbogenerator include separate controllers for controlling fuel supplied to the combustor and power output from the generator. The power controller generates a fuel command based on the required turbine exhaust temperature, where the fuel command is independent of the particular fuel being used. Fuels may include natural gas, diesel, propane, waste gas, or gasoline, for example. The power controller communicates the fuel command and the airflow or calculated air/fuel ratio to the fuel controller which selects an appropriate mode of operation for the injectors. Injector operating modes include one or more pilot modes where fuel is not mixed with air prior to combustion, and one or more premix modes where fuel is highly mixed with air prior to combustion. The fuel controller implements closed-loop feedback control of a fuel metering device and controls the fuel injectors in the appropriate operating mode based on the fuel command, the energy content of the fuel being used, and the air/fuel ratio.
摘要翻译：用于多燃料涡轮发电机的模块化控制的系统和方法包括用于控制供应给燃烧器的燃料和来自发电机的功率输出的单独的控制器。功率控制器基于所需的涡轮排气温度产生燃料指令，其中燃料指令独立于所使用的特定燃料。燃料可以包括例如天然气，柴油，丙烷，废气或汽油。功率控制器将燃料命令和气流或计算出的空气/燃料比与燃料控制器通信，燃料控制器为喷射器选择适当的操作模式。喷射器操作模式包括在燃烧之前不与空气混合的一种或多种先导模式，以及在燃烧之前燃料与空气高度混合的一种或多种预混模式。燃料控制器实现燃料计量装置的闭环反馈控制，并且基于燃料命令，正在使用的燃料的能量含量和空气/燃料比来控制燃料喷射器处于适当的操作模式。

5. 发明授权

US6016658A Low emissions combustion system for a gas turbine engine 有权
标题翻译：低排放燃油喷射器
公开(公告)号：US6016658A
公开(公告)日：2000-01-25
申请号：US182966
申请日：1998-10-08
申请人： Jeffrey W. Willis , Guillermo Pont , Bruce L. Alder, Jr.
发明人： Jeffrey W. Willis , Guillermo Pont , Bruce L. Alder, Jr.
IPC分类号： F02C7/232 , F23C99/00 , F23R3/02 , F23R3/06 , F23R3/16 , F23R3/20 , F23R3/28 , F23R3/42 , F23R3/14 , F23R3/32 , F23R3/36
CPC分类号： F23R3/286 , F23R3/02 , F23R3/16 , F23R3/42
摘要： A low emissions combustion system for a gas turbine engine, including a generally annular combustor with a plurality of tangential fuel injectors to introduce a fuel/air mixture. The annular combustor includes a skirt shaped flow control baffle from the inner liner and air dilution holes in the inner liner underneath the flow control baffle and also in the cylindrical outer liner. The fuel injectors extend through the recuperator housing and into the combustor through an angled tube and then through a tangential guide in the cylindrical outer liner of the combustor housing. The fuel injectors generally comprise an elongated injector tube with the outer end including a coupler having at least one fuel inlet tube. Compressed combustion air is provided to the interior of the elongated injector tube from either holes or slits therein which receive compressed air from the angled tube around the fuel injector which is open to the space between the recuperator housing and the combustor.
摘要翻译：一种用于燃气涡轮发动机的低排放燃烧系统，包括具有多个切向燃料喷射器以引入燃料/空气混合物的大体上环形的燃烧器。环形燃烧器包括来自内衬的裙形流动控制挡板和在流动控制挡板下方的内衬里以及圆柱形外衬里中的空气稀释孔。燃料喷射器通过成角度的管延伸通过换热器壳体并进入燃烧器，然后通过燃烧器壳体的圆柱形外衬里中的切向导向件延伸。燃料喷射器通常包括细长的喷射器管，其外端包括具有至少一个燃料入口管的联接器。压缩的燃烧空气从其中的孔或狭缝中的任一孔或狭缝提供到细长的注射器管的内部，其接收压缩空气，所述压缩空气围绕燃料喷射器，该角度的管围绕换热器壳体和燃烧器之间的空间。

6. 发明授权

US06960840B2 Integrated turbine power generation system with catalytic reactor 有权
标题翻译：具有催化反应器的集成涡轮机发电系统
公开(公告)号：US06960840B2
公开(公告)日：2005-11-01
申请号：US10706070
申请日：2003-11-13
申请人： Jeffrey W. Willis , Paul Berner , Guillermo Pont , Joel Wacknov
发明人： Jeffrey W. Willis , Paul Berner , Guillermo Pont , Joel Wacknov
IPC分类号： F02C3/22 , F02C7/236 , H02J1/10 , H02J1/14 , H02K9/00
CPC分类号： F02C7/2365 , F02C3/22 , H02J1/10 , H02J1/14 , Y02E20/14
摘要： The invention provides integrated turbogenerators having a turbine wheel, a compressor impeller, and a motor generator mounted to or mechanically constrained to a common shaft, and improved components and configurations thereof.
摘要翻译：本发明提供了具有涡轮机叶轮，压缩机叶轮和安装到或机械地限制在公共轴上的电动发电机的集成涡轮发电机及其改进的部件和构造。

7. 发明授权

US5850732A Low emissions combustion system for a gas turbine engine 失效
标题翻译：燃气轮机的低排放燃烧系统
公开(公告)号：US5850732A
公开(公告)日：1998-12-22
申请号：US855210
申请日：1997-05-13
申请人： Jeffrey W. Willis , Guillermo Pont , Bruce L. Alder, Jr.
发明人： Jeffrey W. Willis , Guillermo Pont , Bruce L. Alder, Jr.
IPC分类号： F02C7/232 , F23C99/00 , F23R3/02 , F23R3/06 , F23R3/16 , F23R3/20 , F23R3/28 , F23R3/42 , F02G3/00 , F02C3/08
CPC分类号： F23R3/286 , F23R3/02 , F23R3/16 , F23R3/42
摘要： A low emissions combustion system for a gas turbine engine, including a generally annular combustor with a plurality of tangential fuel injectors (14) to introduce a fuel/air mixture. The annular combustor includes a skirt shaped flow control baffle (48) from the inner liner and air dilution holes (50-54) in the inner liner underneath the flow control baffle and also in the cylindrical outer liner. The fuel injectors (14) extend through the recuperator housing and into the combustor through an angled tube and then through a tangential guide in the cylindrical outer liner of the combustor housing. The fuel injectors generally comprise an elongated injector tube with the outer end including a coupler having at least one fuel inlet tube. Compressed combustion air is provided to the interior of the elongated injector tube from either holes or slits therein which receive compressed air from the angled tube around the fuel injector which is open to the space between the recuperator housing and the combustor.
摘要翻译：一种用于燃气涡轮发动机的低排放燃烧系统，包括具有多个切向燃料喷射器（14）的大致环形的燃烧器，以引入燃料/空气混合物。环形燃烧器包括来自内衬的裙形流动控制挡板（48）和位于流动控制挡板下方的内衬里以及圆柱形外衬里中的空气稀释孔（50-54）。燃料喷射器（14）通过成角度的管延伸通过换热器壳体并进入燃烧器，然后通过燃烧器壳体的圆柱形外衬里中的切向引导件延伸。燃料喷射器通常包括细长的喷射器管，其外端包括具有至少一个燃料入口管的联接器。压缩的燃烧空气从其中的孔或狭缝中的任一孔或狭缝提供到细长的注射器管的内部，其接收压缩空气，所述压缩空气围绕燃料喷射器，该角度的管围绕换热器壳体和燃烧器之间的空间。

8. 发明授权

US06684642B2 Gas turbine engine having a multi-stage multi-plane combustion system 有权
标题翻译：具有多级多平面燃烧系统的燃气轮机
公开(公告)号：US06684642B2
公开(公告)日：2004-02-03
申请号：US10171684
申请日：2002-06-17
申请人： Jeffrey W. Willis , Guillermo Pont , Benjamin E. Toby , Robert D. McKeirnan, Jr.
发明人： Jeffrey W. Willis , Guillermo Pont , Benjamin E. Toby , Robert D. McKeirnan, Jr.
IPC分类号： F02C300
CPC分类号： F23R3/50 , F23R3/16 , F23R3/286 , F23R3/34
摘要： A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
摘要翻译：一种具有多个切向燃料喷射器的低排放燃烧系统，用于在两个间隔开的喷射器平面中的环形燃烧室的燃烧器圆顶端处引入燃料/空气混合物。每个间隔开的喷射器平面包括将预混燃料和空气输送到环形燃烧器中的多个切向燃料喷射器。大致裙形流动控制挡板从锥形内衬延伸到燃料喷射器平面下游的环形燃烧室。在流动控制挡板下方的锥形内衬中的多个空气稀释孔将稀释空气引入环形燃烧室，而圆柱形外衬套中的另外多个空气稀释孔在流动控制挡板下游引入更多的稀释空气。

9. 发明授权

US5894720A Low emissions combustion system for a gas turbine engine employing flame stabilization within the injector tube 有权
标题翻译：用于燃气涡轮发动机的低排放燃烧系统，其在喷射管内使用火焰稳定
公开(公告)号：US5894720A
公开(公告)日：1999-04-20
申请号：US168299
申请日：1998-10-07
申请人： Jeffrey W. Willis , Guillermo Pont , Bruce L. Alder, Jr.
发明人： Jeffrey W. Willis , Guillermo Pont , Bruce L. Alder, Jr.
IPC分类号： F02C7/232 , F23C99/00 , F23R3/02 , F23R3/06 , F23R3/16 , F23R3/20 , F23R3/28 , F23R3/42 , F23R3/54
CPC分类号： F23R3/286 , F23R3/02 , F23R3/16 , F23R3/42
摘要： A low emissions combustion system for a gas turbine engine, including a generally annular combustor with a plurality of tangential fuel injectors to introduce a fuel/air mixture. The annular combustor includes a skirt shaped flow control baffle from the inner liner and air dilution holes in the inner liner underneath the flow control baffle and also in the cylindrical outer liner. The fuel injectors extend through the recuperator housing and into the combustor through an angled tube and then through a tangential guide in the cylindrical outer liner of the combustor housing. The fuel injectors generally comprise an elongated injector tube with the outer end including a coupler having at least one fuel inlet tube. Compressed combustion air is provided to the interior of the elongated injector tube from either holes or slits therein which receive compressed air from the angled tube around the fuel injector which is open to the space between the recuperator housing and the combustor. Flame stabilization occurs outside the injector tube at full power and flashback occurs such the flame stabilization occurs within the injector tube at low power.
摘要翻译：一种用于燃气涡轮发动机的低排放燃烧系统，包括具有多个切向燃料喷射器以引入燃料/空气混合物的大体上环形的燃烧器。环形燃烧器包括来自内衬的裙形流动控制挡板和在流动控制挡板下方的内衬里以及圆柱形外衬里中的空气稀释孔。燃料喷射器通过成角度的管延伸通过换热器壳体并进入燃烧器，然后通过燃烧器壳体的圆柱形外衬里中的切向导向件延伸。燃料喷射器通常包括细长的喷射器管，其外端包括具有至少一个燃料入口管的联接器。压缩的燃烧空气从其中的孔或狭缝中的任一孔或狭缝提供到细长的注射器管的内部，其接收压缩空气，所述压缩空气围绕燃料喷射器，该角度的管围绕换热器壳体和燃烧器之间的空间。火焰稳定在全功率下发生在注射管外部，发生闪回，使得在低功率下在喷射管内发生火焰稳定。

10. 发明授权

US06453658B1 Multi-stage multi-plane combustion system for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的多级多平面燃烧系统
公开(公告)号：US06453658B1
公开(公告)日：2002-09-24
申请号：US09512986
申请日：2000-02-24
申请人： Jeffery W. Willis , Guillermo Pont , Benjamin E. Toby , Robert D. McKeirnan, Jr.
发明人： Jeffery W. Willis , Guillermo Pont , Benjamin E. Toby , Robert D. McKeirnan, Jr.
IPC分类号： F02C300
CPC分类号： F23R3/50 , F23R3/16 , F23R3/286 , F23R3/34
摘要： A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
摘要翻译：一种具有多个切向燃料喷射器的低排放燃烧系统，用于在两个间隔开的喷射器平面中的环形燃烧室的燃烧器圆顶端处引入燃料/空气混合物。每个间隔开的喷射器平面包括将预混燃料和空气输送到环形燃烧器中的多个切向燃料喷射器。大致裙形流动控制挡板从锥形内衬延伸到燃料喷射器平面下游的环形燃烧室。在流动控制挡板下方的锥形内衬中的多个空气稀释孔将稀释空气引入环形燃烧室，而圆柱形外衬套中的另外多个空气稀释孔在流动控制挡板下游引入更多的稀释空气。

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