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1. 发明申请

US20060010878A1 Method of cooling centerbody of premixing burner 失效
标题翻译：预混燃烧器中心体冷却方法
公开(公告)号：US20060010878A1
公开(公告)日：2006-01-19
申请号：US11206029
申请日：2005-08-18
申请人： Stanley Widener
发明人： Stanley Widener
IPC分类号： F02C7/22
CPC分类号： F23R3/286 , F23D14/78
摘要： A gas-air premixing burner for gas turbines includes an air swirler and an annular burner tube surrounding a bluff centerbody. The bluff body serves to stabilize the flame by defining a recirculating vortex. Cooling air is directed to impinge against the bluff face of the centerbody and the spent impingement cooling air flows in a reverse direction towards the air swirler within the centerbody and is discharged through holes at the outer diameter of the centerbody, where it mixes with the fuel/air mixture prior to reaching the flame zone.
摘要翻译：用于燃气轮机的气体 - 空气预混合燃烧器包括一个空气旋流器和一个围绕着虚张声势中心体的环形燃烧器管。非流线形体用于通过限定再循环涡流来稳定火焰。冷却空气被引导以撞击中心体的虚张声光的表面，而消耗的冲击冷却空气朝向中心体内的空气旋流器的相反方向流动，并且通过中心体的外径处的孔排出，其中与燃料混合 /空气混合物到达火焰区域。

2. 发明申请

US20060080966A1 Low-cost dual-fuel combustor and related method 失效
公开(公告)号：US20060080966A1
公开(公告)日：2006-04-20
申请号：US10963724
申请日：2004-10-14
申请人： Stanley Widener
发明人： Stanley Widener
IPC分类号： F02C3/30
CPC分类号： F23L7/00 , F02C3/20 , F23C2900/07001 , F23D17/002 , F23D2209/30 , F23D2900/00008 , F23L2900/07008 , F23R3/286
摘要： A combustor for a gas turbine includes a combustion chamber and a plurality of radially outer nozzles surrounding a single, center nozzle, the radially outer nozzles configured to supply only gas fuel to the combustion chamber and the center nozzle configured to supply both gas and liquid fuel to the combustion chamber.

3. 发明申请

US20050268616A1 Swirler configurations for combustor nozzles and related method 有权
标题翻译：燃烧器喷嘴旋流器配置及相关方法
公开(公告)号：US20050268616A1
公开(公告)日：2005-12-08
申请号：US10859238
申请日：2004-06-03
申请人： Stanley Widener
发明人： Stanley Widener
IPC分类号： F23R3/14 , F23R3/28
CPC分类号： F23R3/286 , F23C2900/07001 , F23R3/14
摘要： A combustor includes a center nozzle surrounded by a plurality of outer nozzles, the center nozzle and each of the outer nozzles having a fuel passage and an air passage, with a swirler surrounding the fuel passage and having a plurality of vanes projecting radially within the air passage, each vane having a trailing edge arranged at a swirl angle relative to a longitudinal axis of the nozzle, wherein the swirl angle for the swirler in the center nozzle is different than the swirl angle for the swirlers in the plurality of outer nozzles.
摘要翻译：燃烧器包括由多个外部喷嘴包围的中心喷嘴，中心喷嘴和每个外部喷嘴具有燃料通道和空气通道，旋流器围绕燃料通道并且具有在空气中径向突出的多个叶片每个叶片具有相对于喷嘴的纵向轴线以旋转角度布置的后缘，其中中心喷嘴中的旋流器的旋转角度不同于多个外部喷嘴中的旋流器的旋转角度。

4. 发明申请

US20050268615A1 METHOD AND APPARATUS FOR COOLING COMBUSTOR LINER AND TRANSITION PIECE OF A GAS TURBINE 有权
标题翻译：用于冷却燃气轮机和气体涡轮机过渡部件的方法和装置
公开(公告)号：US20050268615A1
公开(公告)日：2005-12-08
申请号：US10907866
申请日：2005-04-19
申请人： Ronald Bunker , Jeremy Bailey , Stanley Widener , Thomas Johnson , John Intile
发明人： Ronald Bunker , Jeremy Bailey , Stanley Widener , Thomas Johnson , John Intile
IPC分类号： F23R3/06 , F02C7/12 , F02C7/18 , F23R3/00 , F23R3/30 , F23R3/42
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/03042 , F23R2900/03044
摘要： A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.
摘要翻译：一种用于冷却燃烧器衬套和燃气轮机的过渡件的方法和设备包括具有多个湍流器的燃烧器衬套，该多个湍流器沿着限定燃烧器衬套的长度并位于其外表面上的长度轴向排列; 围绕所述燃烧器衬套的第一流动套筒，其间具有第一流动环空，所述第一流动套筒具有围绕所述第一流动套筒的圆周形成的多排冷却孔，用于将冷却空气从所述压缩机排出口引导到所述第一流动环空中; 连接到所述燃烧器衬套并适于将热燃烧气体运送到所述涡轮机的级的过渡件; 围绕所述过渡件的第二流动套筒，用于将冷却空气引导到所述第二流动套筒和所述过渡件之间的第二流动环空中的第二多排冷却孔; 其中所述第一多个冷却孔和第二多个冷却孔分别配置有有效区域以将小于50％的压缩机排出空气分配到所述第一流动套筒并与来自所述第二流动环的冷却空气混合。

5. 发明申请

US20060191268A1 METHOD AND APPARATUS FOR COOLING GAS TURBINE FUEL NOZZLES 审中-公开
标题翻译：用于冷却燃气涡轮燃料喷嘴的方法和装置
公开(公告)号：US20060191268A1
公开(公告)日：2006-08-31
申请号：US10906588
申请日：2005-02-25
申请人： Stanley Widener , Thomas Johnson
发明人： Stanley Widener , Thomas Johnson
IPC分类号： F02C7/22
CPC分类号： F23D14/48 , F23D14/78 , F23R3/283 , F23R2900/03044
摘要： A method and apparatus for a nozzle of a gas turbine engine is disclosed that facilitates extending a useful life of the nozzle. The method and apparatus include an impingement baffle plate disposed at a back side of a diffusion tip of the nozzle. The method and apparatus includes the impingement baffle plate formed with an array of orifices creating jets for fuel or purge air to impinge on the diffusion tip. In this manner, cooling via convection through diffusion orifices in the diffusion tip is preserved, and cooling is made more robust.
摘要翻译：公开了一种用于燃气涡轮发动机的喷嘴的方法和装置，其有助于延长喷嘴的使用寿命。该方法和装置包括设置在喷嘴的扩散尖端的后侧的冲击挡板。该方法和装置包括形成有阵列的冲击挡板，所述孔阵列产生用于燃料或吹扫空气冲击扩散尖端的喷嘴。以这种方式，通过扩散尖端中的扩散孔的对流冷却被保留，并且使冷却变得更坚固。

6. 发明申请

US20050268614A1 PREMIXING BURNER WITH IMPINGEMENT COOLED CENTERBODY AND METHOD OF COOLING CENTERBODY 失效
标题翻译：具有冲击冷却中心的预热式燃烧器和冷却中心体的方法
公开(公告)号：US20050268614A1
公开(公告)日：2005-12-08
申请号：US10859232
申请日：2004-06-03
申请人： Stanley Widener
发明人： Stanley Widener
IPC分类号： F23R3/28 , F02C7/22 , F02C7/232 , F23D14/48 , F23R3/14
CPC分类号： F23R3/286 , F23D14/78
摘要： A gas-air premixing burner for gas turbines includes an air swirler and an annular burner tube surrounding a bluff centerbody. The bluff body serves to stabilize the flame by defining a recirculating vortex. Cooling air is directed to impinge against the bluff face of the centerbody and the spent impingement cooling air flows in a reverse direction towards the air swirler within the centerbody and is discharged through holes at the outer diameter of the centerbody, where it mixes with the fuel/air mixture prior to reaching the flame zone.
摘要翻译：用于燃气轮机的气体 - 空气预混合燃烧器包括一个空气旋流器和一个围绕着虚张声势中心体的环形燃烧器管。非流线形体用于通过限定再循环涡流来稳定火焰。冷却空气被引导以撞击中心体的虚张声光的表面，而消耗的冲击冷却空气朝向中心体内的空气旋流器的相反方向流动，并且通过中心体的外径处的孔排出，其中与燃料混合 /空气混合物到达火焰区域。

7. 发明申请

US20110197591A1 AXIALLY STAGED PREMIXED COMBUSTION CHAMBER 审中-公开
标题翻译：轴向预热燃烧室
公开(公告)号：US20110197591A1
公开(公告)日：2011-08-18
申请号：US13025307
申请日：2011-02-11
申请人： Almaz Valeev , Sergey Anatolievich Meshkov , Mark Hadley , Stanley Widener , Geoffrey Myers , Valery Alexandrovich Mitrofanov
发明人： Almaz Valeev , Sergey Anatolievich Meshkov , Mark Hadley , Stanley Widener , Geoffrey Myers , Valery Alexandrovich Mitrofanov
IPC分类号： F23R3/28
CPC分类号： F23R3/46 , F23R3/286 , F23R3/343
摘要： A combustor for a gas turbine includes a plurality of radially outer nozzles arranged in an annular array, each of the radially outer nozzles having an outlet end located to supply fuel and/or air to a first combustion chamber. A center nozzle has an outlet end located axially upstream of the outlet ends of the radially outer nozzles, and is configured and arranged to supply fuel and air to a second combustion chamber axially upstream of the first combustion chamber. The second combustion chamber opens into the first combustion chamber and has a length sufficient to maintain a center nozzle flame confined to the second combustion chamber.
摘要翻译：用于燃气涡轮机的燃烧器包括布置成环形阵列的多个径向外部喷嘴，每个径向外部喷嘴具有位于将燃料和/或空气供应到第一燃烧室的出口端。中心喷嘴具有位于径向外部喷嘴的出口端的轴向上游的出口端，并且构造和布置成将燃料和空气供应到在第一燃烧室的轴向上游的第二燃烧室。第二燃烧室通向第一燃烧室，并具有足以将中心喷嘴火焰保持在第二燃烧室中的长度。

8. 发明申请

US20060042255A1 COMBUSTOR COOLING WITH ANGLED SEGMENTED SURFACES 有权
标题翻译： COMBUSTOR冷却与安装的边界表面
公开(公告)号：US20060042255A1
公开(公告)日：2006-03-02
申请号：US10711131
申请日：2004-08-26
申请人： Ronald Bunker , Jeremy Bailey , Stanley Widener , Thomas Johnson
发明人： Ronald Bunker , Jeremy Bailey , Stanley Widener , Thomas Johnson
IPC分类号： F23R3/42
CPC分类号： F02C7/12 , F01D25/12 , F01D25/14 , F02C7/18 , F05D2240/35 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , F23R3/005
摘要： A combustor liner for a gas turbine includes a body having a plurality of angled strips on an outside surface of the combustor liner. The plurality of angled strips are arranged in an array about the outside surface. A space is disposed between each of said plurality of angled strips so as to create vortices in a cooling air flowing in a longitudinal direction across said outside surface of said combustor liner. A method of fabricating a combustor liner includes forming a plurality of angled strips on an outside surface of the combustor liner and arranged in an array about the outside surface, each of the angled strips is disposed so as to be spaced apart to create vortices in a cooling air flowing across the outside surface of the combustor liner.
摘要翻译：用于燃气轮机的燃烧器衬套包括在燃烧器衬套的外表面上具有多个成角度的条带的主体。多个成角度的条带围绕外表面布置成阵列。在所述多个成角度的条带中的每一个之间设置一个空间，以便在穿过所述燃烧器衬套的所述外表面沿纵向方向流动的冷却空气中产生涡流。一种制造燃烧器衬套的方法包括在燃烧器衬套的外表面上形成多个成角度的带，并围绕外表面排列成阵列，每个成角度的带被设置为间隔开以形成涡流流过燃烧器衬套的外表面的冷却空气。

9. 发明申请

US20050268618A1 BURNER TUBE AND METHOD FOR MIXING AIR AND GAS IN A GAS TURBINE ENGINE 失效
标题翻译：用于混合气体涡轮发动机中的空气和燃气的燃烧器管和方法
公开(公告)号：US20050268618A1
公开(公告)日：2005-12-08
申请号：US10862427
申请日：2004-06-08
申请人： Thomas Johnson , Stanley Widener , Kevin McMahan
发明人： Thomas Johnson , Stanley Widener , Kevin McMahan
IPC分类号： F23R3/20 , F23D14/62 , F23R3/14 , F23R3/28 , F23R3/30 , F23R3/34
CPC分类号： F23R3/14 , F23C2900/07001 , F23R3/286
摘要： A hybrid structure that combines characteristics of the DACRS and Swozzle burners to provide the high mixing ability of an axial flowing counter rotating vane swirler with good dynamic flame stability characteristics of a bluff center body.
摘要翻译：一种混合结构，结合了DACRS和Swozzle燃烧器的特性，提供了具有良好动态火焰稳定性的非流线型中心体的轴流式逆向旋转叶片旋流器的高混合能力。

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