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1. 发明授权

US07712314B1 Venturi cooling system 有权
标题翻译：文丘里冷却系统
公开(公告)号：US07712314B1
公开(公告)日：2010-05-11
申请号：US12357029
申请日：2009-01-21
申请人： John Barnes , Adam Bailey , John Battaglioli , Robert Bland
发明人： John Barnes , Adam Bailey , John Battaglioli , Robert Bland
IPC分类号： F23R3/28
CPC分类号： F23R3/002 , F23R3/04 , F23R3/42 , Y02T50/675
摘要： A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines a passageway therein having a first side facing the nozzle and a second side facing the combustion chamber. Compressed air is directed into an inlet in fluid communication with the first and second sides of the venturi passageway. The venturi passageway directs the compressed air from the inlet in opposite directions within the first and second sides of the passageway for cooling the venturi.
摘要翻译：提供了一种用于燃气轮机的燃烧器，其具有位于一端的喷嘴组件和限定燃烧器的第二端的燃烧室。文丘里管位于燃烧室内，在喷嘴和燃烧室之间。文氏管在其中限定通道，其具有面向喷嘴的第一侧和面向燃烧室的第二侧。压缩空气被引导到与文氏管通道的第一和第二侧流体连通的入口。文氏管通道在通道的第一和第二侧内沿相反方向引导来自入口的压缩空气，以冷却文丘里管。

2. 发明授权

US07707836B1 Venturi cooling system 有权
标题翻译：文丘里冷却系统
公开(公告)号：US07707836B1
公开(公告)日：2010-05-04
申请号：US12536861
申请日：2009-08-06
申请人： John Barnes , Adam Bailey , John Battaglioli , Robert Bland
发明人： John Barnes , Adam Bailey , John Battaglioli , Robert Bland
IPC分类号： F23R3/42
CPC分类号： F23R3/002 , F23R3/04 , F23R3/42 , Y02T50/675
摘要： A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines an internal passageway therein having a first side facing the nozzle and a second side facing the combustion chamber. Compressed air is directed into an inlet in fluid communication with the first and second sides of the internal passageway. The internal passageway directs the compressed air from the inlet in opposite directions within the first and second sides of the internal passageway for cooling the venturi.
摘要翻译：提供了一种用于燃气轮机的燃烧器，其具有位于一端的喷嘴组件和限定燃烧器的第二端的燃烧室。文丘里管位于燃烧室内，在喷嘴和燃烧室之间。文氏管在其中限定内部通道，其中具有面向喷嘴的第一侧和面向燃烧室的第二侧。压缩空气被引导到与内部通道的第一和第二侧流体连通的入口。内部通道在内部通道的第一和第二侧内沿相反方向将压缩空气从入口引导，以冷却文丘里管。

3. 发明申请

US20110239654A1 ANGLED SEAL COOLING SYSTEM 审中-公开
标题翻译： ANGLED密封冷却系统
公开(公告)号：US20110239654A1
公开(公告)日：2011-10-06
申请号：US12755137
申请日：2010-04-06
申请人： Robert Bland , John Battaglioli , John Barnes , Andrew Hamer
发明人： Robert Bland , John Battaglioli , John Barnes , Andrew Hamer
IPC分类号： F02C7/18
CPC分类号： F23R3/002
摘要： An aft liner seal for a combustor for a gas turbine includes an inner shell having an inner and outer surface and central axis. The aft liner seal has an outer shell positioned over the inner shell that has an inner and outer surface and central axis coaxial with the inner shell. One of the outer surface of the inner shell or the inner surface of the outer shell has grooves angled relative to the central axis. The angled grooves and adjacent portions of the inner surface of the outer shell or the outer surface of the inner shell form cooling passages. The cooling air exits the cooling passages at an exit angle that is matched to a swirl angle of the combustor flow. Matching of the exit angle and the swirl angle minimizes shear of cooling air with respect to flow exiting the combustor liner.
摘要翻译：用于燃气轮机的燃烧器的后衬套密封件包括具有内表面和外表面以及中心轴线的内壳。尾衬密封件具有定位在内壳上方的外壳，其具有与内壳同轴的内表面和外表面以及中心轴线。内壳的外表面或外壳的内表面之一具有相对于中心轴线成角度的槽。外壳的内表面或内壳的外表面的成角度的槽和相邻部分形成冷却通道。冷却空气以与燃烧器流动的旋转角度匹配的出口角度离开冷却通道。出口角和旋转角度的匹配使冷却空气相对于离开燃烧器衬套的流动的剪切最小化。

4. 发明授权

US07707833B1 Combustor nozzle 有权
标题翻译：燃烧器喷嘴
公开(公告)号：US07707833B1
公开(公告)日：2010-05-04
申请号：US12535262
申请日：2009-08-04
申请人： Robert Bland , John Battaglioli
发明人： Robert Bland , John Battaglioli
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/286 , F23D14/64
摘要： A secondary nozzle is provided for a gas turbine. The secondary nozzle includes a flange and an elongated nozzle body extending from the flange. At least one premix fuel injector is spaced radially from the nozzle body and extends from the flange generally parallel to the nozzle body. At least one second nozzle tube is fluidly connected to the fuel source and spaced radially outward from the first nozzle tube with a proximal end fixed to the flange. The second nozzle tube has a distal end, spaced from the proximal end, with at least one aperture therein. A passageway extends between the proximal end and the distal end of the second nozzle tube, with the passageway fluidly connecting to the fuel source and the aperture.
摘要翻译：为燃气轮机设置二次喷嘴。辅助喷嘴包括凸缘和从凸缘延伸的细长喷嘴体。至少一个预混合燃料喷射器与喷嘴体径向间隔开并且从凸缘大致平行于喷嘴体延伸。至少一个第二喷嘴管流体地连接到燃料源并且与第一喷嘴管径向向外间隔开，而近端固定在凸缘上。第二喷嘴管具有与近端间隔开的远端，其中至少有一个孔。通道在第二喷嘴管的近端和远端之间延伸，通道流体地连接到燃料源和孔。

5. 发明申请

US20070227148A1 Air flow conditioner for a combustor can of a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的燃烧室的气流调节器
公开(公告)号：US20070227148A1
公开(公告)日：2007-10-04
申请号：US11397364
申请日：2006-04-04
申请人： Robert Bland , John Battaglioli , Anil Gulati , Stephen Ramier
发明人： Robert Bland , John Battaglioli , Anil Gulati , Stephen Ramier
IPC分类号： F23R3/00
CPC分类号： F23R3/04
摘要： A burner (27) of a gas turbine engine (10) includes a cylindrical basket (60) comprising an air flow reversal region (86). The flow reversal region ends at an air inlet plane (84) of the basket. The burner also includes a flow conditioner (90) disposed in the flow reversal region transecting an air flow (80) flowing non-uniformly through the flow reversal region, the flow conditioner being effective to mitigate variation of the air flow entering the basket across the inlet plane.
摘要翻译：燃气涡轮发动机（10）的燃烧器（27）包括包括气流反转区域（86）的圆柱形篮（60）。流动反转区域在篮的空气入口平面（84）处终止。燃烧器还包括设置在流动反向区域中的流动调节器（90），其横切不均匀地流过流动反向区域的空气流（80），流动调节器有效地减轻进入篮子的空气流的变化入口平面。

6. 发明授权

US08499565B2 Axial diffusor for a turbine engine 有权
标题翻译：涡轮发动机的轴向扩散器
公开(公告)号：US08499565B2
公开(公告)日：2013-08-06
申请号：US12572043
申请日：2009-10-01
申请人： Robert Bland , John Battaglioli
发明人： Robert Bland , John Battaglioli
IPC分类号： F02C3/04 , F23R3/42 , F23R3/54
CPC分类号： F01D9/023 , F04D29/541 , F05D2260/221
摘要： A turbine engine having a plenum for passing fluids from an outlet of a compressor to an inlet of a combustor that may increase the efficiency of the turbine engine. The turbine engine may include a combustor, a compressor positioned upstream of the combustor, a transition channel extending from the compressor to the combustor, and a shell extending between the compressor and a combustor portal and positioned around the at least one transition channel. The turbine engine may also include an axial diffusor in the shell near the at least one transition channel, wherein the axial diffusor may include a fluid flow recess in a trailing edge of the axial diffusor. The turbine engine may also include a wave protrusion extending from a surface positioned radially inward of the axial diffusor. The fluid flow recess and the wave protrusion may reduce fluid flow loss within the shell.
摘要翻译：具有用于将流体从压缩机的出口传递到燃烧器的入口的涡轮发动机，其可以提高涡轮发动机的效率。涡轮发动机可以包括燃烧器，位于燃烧器上游的压缩机，从压缩机延伸到燃烧器的过渡通道，以及在压缩机和燃烧器入口之间延伸并围绕至少一个过渡通道定位的壳体。涡轮发动机还可以包括靠近至少一个过渡通道的壳体中的轴向扩散器，其中轴向扩散器可以包括在轴向扩散器的后缘中的流体流动凹部。涡轮发动机还可以包括从位于轴向扩散器的径向内侧的表面延伸的波浪突起。流体流动凹槽和波浪突起可以减少壳体内的流体流动损失。

7. 发明申请

US20100192582A1 COMBUSTOR NOZZLE 审中-公开
标题翻译： COMBUSTOR喷嘴
公开(公告)号：US20100192582A1
公开(公告)日：2010-08-05
申请号：US12365539
申请日：2009-02-04
申请人： Robert Bland , John Battaglioli
发明人： Robert Bland , John Battaglioli
IPC分类号： F02C1/00
CPC分类号： F23R3/286 , F23D14/64
摘要： A secondary nozzle is provided for a gas turbine. The secondary nozzle includes a flange and an elongated nozzle body extending from the flange. At least one premix fuel injector is spaced radially from the nozzle body and extends from the flange generally parallel to the nozzle body. At least one second nozzle tube is fluidly connected to the fuel source and spaced radially outward from the first nozzle tube with a proximal end fixed to the flange. The second nozzle tube has a distal end, spaced from the proximal end, with at least one aperture therein. A passageway extends between the proximal end and the distal end of the second nozzle tube, with the passageway fluidly connecting to the fuel source and the aperture.
摘要翻译：为燃气轮机设置二次喷嘴。辅助喷嘴包括凸缘和从凸缘延伸的细长喷嘴体。至少一个预混合燃料喷射器与喷嘴体径向间隔开并且从凸缘大致平行于喷嘴体延伸。至少一个第二喷嘴管流体地连接到燃料源并且与第一喷嘴管径向向外间隔开，而近端固定在凸缘上。第二喷嘴管具有与近端间隔开的远端，其中至少有一个孔。通道在第二喷嘴管的近端和远端之间延伸，通道流体地连接到燃料源和孔。

8. 发明申请

US20070214792A1 Axial diffusor for a turbine engine 审中-公开
标题翻译：涡轮发动机的轴向扩散器
公开(公告)号：US20070214792A1
公开(公告)日：2007-09-20
申请号：US11378028
申请日：2006-03-17
申请人： Robert Bland , John Battaglioli
发明人： Robert Bland , John Battaglioli
IPC分类号： F02C1/00
CPC分类号： F01D9/023 , F05D2260/221
摘要： A turbine engine having a plenum for passing fluids from an outlet of a compressor to an inlet of a combustor that may increase the efficiency of the turbine engine. The turbine engine may include a combustor, a compressor positioned upstream of the combustor, a transition channel extending from the compressor to the combustor, and a shell extending between the compressor and a combustor portal and positioned around the at least one transition channel. The turbine engine may also include an axial diffusor in the shell near the at least one transition channel, wherein the axial diffusor may include a fluid flow recess in a leading edge of the axial diffusor. The turbine engine may also include a wave protrusion extending from a surface positioned radially inward of the axial diffusor. The fluid flow recess and the wave protrusion may reduce fluid flow loss within the shell.
摘要翻译：具有用于将流体从压缩机的出口传递到燃烧器的入口的涡轮发动机，其可以提高涡轮发动机的效率。涡轮发动机可以包括燃烧器，位于燃烧器上游的压缩机，从压缩机延伸到燃烧器的过渡通道，以及在压缩机和燃烧器入口之间延伸并围绕至少一个过渡通道定位的壳体。涡轮发动机还可以包括靠近至少一个过渡通道的壳体中的轴向扩散器，其中轴向扩散器可以包括在轴向扩散器的前缘中的流体流动凹部。涡轮发动机还可以包括从位于轴向扩散器的径向内侧的表面延伸的波浪突起。流体流动凹槽和波浪突起可以减少壳体内的流体流动损失。

9. 发明申请

US20100058768A1 AXIAL DIFFUSOR FOR A TURBINE ENGINE 有权
标题翻译：涡轮发动机的轴流式减震器
公开(公告)号：US20100058768A1
公开(公告)日：2010-03-11
申请号：US12572043
申请日：2009-10-01
申请人： Robert Bland , John Battaglioli
发明人： Robert Bland , John Battaglioli
IPC分类号： F02C7/00
CPC分类号： F01D9/023 , F04D29/541 , F05D2260/221
摘要： A turbine engine having a plenum for passing fluids from an outlet of a compressor to an inlet of a combustor that may increase the efficiency of the turbine engine. The turbine engine may include a combustor, a compressor positioned upstream of the combustor, a transition channel extending from the compressor to the combustor, and a shell extending between the compressor and a combustor portal and positioned around the at least one transition channel. The turbine engine may also include an axial diffusor in the shell near the at least one transition channel, wherein the axial diffusor may include a fluid flow recess in a trailing edge of the axial diffusor. The turbine engine may also include a wave protrusion extending from a surface positioned radially inward of the axial diffusor. The fluid flow recess and the wave protrusion may reduce fluid flow loss within the shell.
摘要翻译：具有用于将流体从压缩机的出口传递到燃烧器的入口的涡轮发动机，其可以提高涡轮发动机的效率。涡轮发动机可以包括燃烧器，位于燃烧器上游的压缩机，从压缩机延伸到燃烧器的过渡通道，以及在压缩机和燃烧器入口之间延伸并围绕至少一个过渡通道定位的壳体。涡轮发动机还可以包括靠近至少一个过渡通道的壳体中的轴向扩散器，其中轴向扩散器可以包括在轴向扩散器的后缘中的流体流动凹部。涡轮发动机还可以包括从位于轴向扩散器的径向内侧的表面延伸的波浪突起。流体流动凹槽和波浪突起可以减少壳体内的流体流动损失。

10. 发明授权

US07096671B2 Catalytic combustion system and method 有权
标题翻译：催化燃烧系统及方法
公开(公告)号：US07096671B2
公开(公告)日：2006-08-29
申请号：US10686458
申请日：2003-10-14
申请人： Robert Bland , Ramarao V. Bandaru , John Battaglioli
发明人： Robert Bland , Ramarao V. Bandaru , John Battaglioli
IPC分类号： F02C7/22 , F02C7/26
CPC分类号： F23R3/40
摘要： Aspects according to the invention relate to a catalytic combustor system for a turbine engine and an associated method. Catalytic combustors are used in connection with turbine engines because they can minimize the formation of oxides of nitrogen during combustion. Despite this emissions advantage, catalytic combustion systems can increase the level of CO in the turbine exhaust. According to aspects of the invention, vortex formation devices includes vortex generators, swirlers and mixers can be placed downstream of each catalytic module surrounding the pilot nozzle so as to form one or more vortices in the otherwise substantially laminar flow exiting the modules. The vortices can create a suction so that a portion of the flow exiting the pilot nozzles is mixed with the flow exiting the catalyst modules. The introduction of the higher temperature pilot flow can accelerate the catalytic reaction time, promoting burnout of the CO formed during combustion.
摘要翻译：根据本发明的方面涉及一种用于涡轮发动机的催化燃烧器系统和相关联的方法。催化燃烧器用于涡轮发动机，因为它们可以在燃烧过程中最小化氮氧化物的形成。尽管这种排放优势，催化燃烧系统可以增加涡轮排气中的CO水平。根据本发明的方面，涡流形成装置包括涡流发生器，旋流器和混合器可以放置在围绕引燃喷嘴的每个催化剂模块的下游，以便在离开模块的基本层流中形成一个或多个涡流。涡流可以产生吸力，使得离开引燃喷嘴的流的一部分与离开催化剂模块的流混合。引入较高温度的先导流可以加速催化反应时间，促进燃烧过程中形成的CO的烧坏。

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