公开(公告)号：US07685823B2

公开(公告)日：2010-03-30

申请号：US11262447

申请日：2005-10-28

申请人： Vincent C. Martling ,  Zhenhua Xiao

发明人： Vincent C. Martling ,  Zhenhua Xiao

IPC分类号： F02C1/00

CPC分类号： F01D9/023 ,  F23R3/04 ,  F23R3/54

摘要： An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.

摘要翻译： 公开了一种提供具有增加的燃烧稳定性并减少跨越燃气轮机燃烧器的压降的燃气轮机燃烧器的装置和方法。 多个叶片在流动套筒和燃烧衬套之间径向固定到流动套管。 多个叶片用于引导进入流动套筒和燃烧衬套之间的区域的空气流在大致轴向方向上，从而去除切向速度的分量，从而提供更均匀的空气流，并减少燃烧室的量 由于试图通过单独的压力降低气流而导致的压力损失。

公开(公告)号：US20050241317A1

公开(公告)日：2005-11-03

申请号：US10836971

申请日：2004-04-30

申请人： Vincent Martling ,  Zhenhua Xiao

发明人： Vincent Martling ,  Zhenhua Xiao

IPC分类号： F01D9/02 ,  F23R3/26 ,  F23R3/42 ,  F23R3/46

CPC分类号： F23R3/46 ,  F01D9/023 ,  F23R3/26

摘要： The present invention provides an apparatus and method for reducing the pressure loss of air prior to entering a combustion system, such that, for a known combustion system having a predetermined pressure loss, the resulting fluid entering the turbine has a higher supply pressure that will result in more efficient turbine and increased engine output. Significant enhancements include the addition of a plurality of deflector assemblies to direct the air from a compressor outlet towards an exposed single-wall transition duct to provide direct cooling to a first panel of the transition duct.

摘要翻译： 本发明提供了一种用于在进入燃烧系统之前减少空气的压力损失的装置和方法，使得对于具有预定压力损失的已知燃烧系统，进入涡轮机的所得流体具有较高的供应压力，这将导致 在更高效的涡轮机和增加的发动机输出。 显着的增强包括添加多个偏转器组件以将空气从压缩机出口朝向暴露的单壁过渡管道引导，以向过渡管道的第一面板提供直接冷却。

公开(公告)号：US20050132708A1

公开(公告)日：2005-06-23

申请号：US10744423

申请日：2003-12-22

申请人： Vincent Martling ,  Zhenhua Xiao

发明人： Vincent Martling ,  Zhenhua Xiao

IPC分类号： F01D9/02 ,  F23R3/42 ,  F23R3/60

CPC分类号： F23R3/60 ,  F01D9/023 ,  F23D2211/00 ,  F23D2214/00 ,  F23R2900/00005 ,  F23R2900/03041

摘要： An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received within the transition duct such that a combustion liner seal is in contact with an inner wall of the transition duct inlet ring. Increasing the dedicated cooling air supply to the combustion liner aft end, coupled with a modified combustion liner aft end geometry, significantly reduces turbulence and flow re-circulation, thereby resulting in lower metal temperatures and increased component life. Multiple embodiments of the interface region are disclosed depending on the amount of cooling required.

摘要翻译： 公开了燃气轮机燃烧器的燃烧衬套和过渡管道之间的界面区域，其具有改进的冷却，使得部件寿命增加并且金属温度降低。 燃烧衬套的后端可伸缩地容纳在过渡管道内，使得燃烧衬套密封件与过渡管道入口环的内壁接触。 增加燃烧衬套后端的专用冷却空气供应，与改进的燃烧衬套后端几何结合，显着减少湍流和流动再循环，从而导致更低的金属温度和增加的部件寿命。 取决于所需的冷却量来公开界面区域的多个实施例。

公开(公告)号：US06832482B2

公开(公告)日：2004-12-21

申请号：US10302229

申请日：2002-11-22

申请人： Vincent C. Martling ,  Zhenhua Xiao

发明人： Vincent C. Martling ,  Zhenhua Xiao

IPC分类号： F23R304

CPC分类号： F23R3/286 ,  F23R3/005

摘要： A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process. In an alternate embodiment, a combustion system is disclosed incorporating a shaped deflector to direct cooling air into a cooling passageway of a venturi. The deflector is configured to provide a cooling system with increased total pressure to increase overall cooling effectiveness.

摘要翻译： 一种用于在燃气涡轮发动机中使用的低NOx排放燃烧器中的文丘里管和燃烧室的冷却空气的方法，该方法包括以下步骤：提供围绕所述燃烧室和文丘里管的环形空气通道，其中所述压力下的冷却空气进入 在燃烧室的后部附近的燃烧室/文丘里管，沿着燃烧室使空气通过文丘里管，其中空气在文丘里管的会聚区域的前部附近离开。 该方法防止任何通道/通道冷却空气被接收到燃烧室中，并且同时在空气已经经过文丘里管的燃烧室并且被加热之后引入冷却空气的出口 从而提高了燃烧器的效率，同时降低和降低了燃烧过程中的NOx排放。 在替代实施例中，公开了一种结合成形偏转器以将冷却空气引导到文氏管的冷却通道中的燃烧系统。 偏转器被配置为提供具有增加的总压力的冷却系统以增加总体冷却效果。

公开(公告)号：US06558114B1

公开(公告)日：2003-05-06

申请号：US09676061

申请日：2000-09-29

申请人： Joseph Theodore Tapley ,  John Y. Xia ,  Zhenhua Xiao

发明人： Joseph Theodore Tapley ,  John Y. Xia ,  Zhenhua Xiao

IPC分类号： F01D1104

CPC分类号： F01D11/001 ,  F01D5/081

摘要： The subcavity between a stator seal assembly and the upstream rotor disc in the interstage disc cavity of a gas turbine is divided into a radially inward region and a radially outward region by an annular baffle that extends from the seal assembly partially across the subcavity toward the rotor disc. The volume of cooling air injected into the interstage disc cavity can be reduced to increase turbine efficiency because the baffle interrupts recirculation in the subcavity to confine ingress of the hot main gas flow to the radially outward region away from the rotor seals.

摘要翻译： 定子密封组件和燃气轮机的级间盘腔中的上游转子盘之间的子腔通过环形挡板分成径向向内的区域和径向向外的区域，该环形挡板从密封组件部分穿过子腔向转子 光盘。 可以减少注入到级间盘腔中的冷却空气的体积，以增加涡轮机的效率，因为挡板中断了子腔中的再循环，从而限制热的主气流进入远离转子密封件的径向向外的区域。

公开(公告)号：US08504276B2

公开(公告)日：2013-08-06

申请号：US12039183

申请日：2008-02-28

申请人： Vincent C. Martling ,  Peter So ,  Zhenhua Xiao ,  Plazi Ricklin

发明人： Vincent C. Martling ,  Peter So ,  Zhenhua Xiao ,  Plazi Ricklin

IPC分类号： F02M63/02

CPC分类号： F02C9/28 ,  F02C9/34 ,  F05D2270/082 ,  F05D2270/303 ,  F05D2270/708 ,  F23N2041/20

摘要： Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.

摘要翻译： 公开了用于控制燃气涡轮发动机以使燃烧动力学和排放最小化的实施例。 提供了用于控制燃气涡轮发动机的方法和装置，其中测量压缩机入口温度并且实时计算涡轮参考温度，并用于确定每个燃料回路的最有效的燃料分流和运行条件。 然后根据所识别的燃料分配来调节燃料回路的燃料流量。

公开(公告)号：US20090222187A1

公开(公告)日：2009-09-03

申请号：US12039183

申请日：2008-02-28

申请人： VINCENT C. MARTLING ,  Peter SO ,  ZHENHUA XIAO ,  PLAZI RICKLIN

发明人： VINCENT C. MARTLING ,  Peter SO ,  ZHENHUA XIAO ,  PLAZI RICKLIN

IPC分类号： F02C9/00

CPC分类号： F02C9/28 ,  F02C9/34 ,  F05D2270/082 ,  F05D2270/303 ,  F05D2270/708 ,  F23N2041/20

摘要： Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.

摘要翻译： 公开了用于控制燃气涡轮发动机以使燃烧动力学和排放最小化的实施例。 提供了用于控制燃气涡轮发动机的方法和装置，其中测量压缩机入口温度并且实时计算涡轮参考温度，并用于确定每个燃料回路的最有效的燃料分流和运行条件。 然后根据所识别的燃料分配来调节燃料回路的燃料流量。

公开(公告)号：US20090139238A1

公开(公告)日：2009-06-04

申请号：US11262447

申请日：2005-10-28

申请人： Vincent C. Martling ,  Zhenhua Xiao

发明人： Vincent C. Martling ,  Zhenhua Xiao

IPC分类号： F02C1/00

CPC分类号： F01D9/023 ,  F23R3/04 ,  F23R3/54

摘要： An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.

摘要翻译： 公开了一种提供具有增加的燃烧稳定性并减少跨越燃气轮机燃烧器的压降的燃气轮机燃烧器的装置和方法。 多个叶片在流动套筒和燃烧衬套之间径向固定到流动套管。 多个叶片用于引导进入流动套筒和燃烧衬套之间的区域的空气流在大致轴向方向上，从而去除切向速度的分量，从而提供更均匀的空气流，并减少燃烧室的量 由于试图通过单独的压力降低气流而导致的压力损失。

公开(公告)号：US07269957B2

公开(公告)日：2007-09-18

申请号：US10857713

申请日：2004-05-28

申请人： Vincent C. Martling ,  Zhenhua Xiao

发明人： Vincent C. Martling ,  Zhenhua Xiao

IPC分类号： F23R3/60

CPC分类号： F23R3/002 ,  F01D9/023 ,  F23R3/46 ,  Y02T50/675

摘要： A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness along the aft end of the combustion liner is improved, resulting in extended component life, while utilizing a simpler combustion liner geometry. The region of the combustion liner proximate its second end comprises a plurality of spring seals that seal against a transition duct while admitting a cooling fluid to pass into a passage, formed between the combustion liner and spring seals, that feeds a plurality of cooling holes located in the combustion liner proximate the liner second end. Depending on the cooling requirements, the cooling holes can be angled both axially and circumferentially to maximize the cooling effectiveness.

摘要翻译： 公开了一种燃气轮机燃烧衬套，其在其与过渡管道之间具有替代的界面区域，其中沿着燃烧衬套的后端的冷却效果得到改善，从而在使用更简单的燃烧衬套几何形状的同时延长了部件的使用寿命。 靠近其第二端的燃烧衬套的区域包括多个弹簧密封件，其在允许冷却流体进入形成在燃烧衬套和弹簧密封件之间的通道中时密封过渡管道，该通道供给多个位于 在靠近衬套第二端的燃烧衬里中。 根据冷却要求，冷却孔可以轴向和周向成角度，以最大化冷却效果。

公开(公告)号：US07137241B2

公开(公告)日：2006-11-21

申请号：US10836972

申请日：2004-04-30

申请人： Vincent C. Martling ,  Zhenhua Xiao

发明人： Vincent C. Martling ,  Zhenhua Xiao

IPC分类号： F02C3/14 ,  F02C7/18

CPC分类号： F23R3/002 ,  F01D9/023 ,  F05D2260/202 ,  F05D2260/203 ,  F05D2260/221 ,  F23R2900/03041

摘要： A gas turbine transition duct having a reduced pressure loss is disclosed. The transition duct of the preferred embodiment comprises a panel assembly having a first panel fixed to a second panel and a mounting assembly for securing the transition duct to a turbine inlet. The first panel includes a means for augmenting the heat transfer from the first panel while the second panel includes a plurality of first cooling holes for directing cooling air through the second panel. Specific details are provided regarding the first cooling holes and multiple embodiments are disclosed for the heat transfer augmentation of the transition duct first panel.

摘要翻译： 公开了一种具有减小的压力损失的燃气轮机过渡管道。 优选实施例的过渡管道包括面板组件，其具有固定到第二面板的第一面板和用于将过渡管道固定到涡轮机入口的安装组件。 第一面板包括用于增加从第一面板传热的装置，而第二面板包括用于引导冷却空气通过第二面板的多个第一冷却孔。 提供关于第一冷却孔的具体细节，并且公开了多个实施例用于过渡管道第一面板的传热增强。