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1. 发明申请

WO2016068922A1 PILOT BURNER AND METHOD FOR STABILIZING A PILOT FLAME IN A COMBUSTOR SUBJECT TO COMBUSTION DYNAMICS 审中-公开
标题翻译：燃烧器和燃烧器燃烧器中的导弹火焰稳定化的方法动力学
公开(公告)号：WO2016068922A1
公开(公告)日：2016-05-06
申请号：PCT/US2014/063045
申请日：2014-10-30
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： RAJARAM, Rajesh , PORTILLO BILBAO, Juan Enrique
IPC分类号： F23R3/34 , F23D11/12 , F23D14/58
CPC分类号： F23D11/12 , F23D14/58 , F23R3/343 , F23R2900/00014
摘要： A pilot burner (15) and method for stabilizing a pilot flame in a combustor (14) of a gas turbine engine are provided. The pilot burner includes a fuel nozzle (17) having at least one orifice having a cross-sectional profile effective to stabilize a pilot flame subject to combustion dynamics. The cross-sectional profile may be a non-circular cross-sectional profile (52, 54) and/or may be formed by an array of neighboring sub-orifices (56), such as circular or non-circular cross-sectional profiles that in combination attain a desired fuel-injecting area.
摘要翻译：提供了一种用于在燃气涡轮发动机的燃烧器（14）中稳定引燃火焰的引燃燃烧器（15）和方法。引燃燃烧器包括燃料喷嘴（17），燃料喷嘴（17）具有至少一个孔口，该孔口具有有效地稳定受到燃烧动力学的引燃火焰的横截面轮廓。横截面轮廓可以是非圆形横截面轮廓（52,54）和/或可以由相邻子孔（56）的阵列形成，例如圆形或非圆形横截面轮廓，其中组合地获得期望的燃料喷射区域。

2. 发明申请

WO2014126758A1 FLOW SLEEVE INLET ASSEMBLY IN A GAS TURBINE ENGINE 审中-公开
标题翻译：一个气体涡轮发动机中的流动套管入口组件
公开(公告)号：WO2014126758A1
公开(公告)日：2014-08-21
申请号：PCT/US2014/014818
申请日：2014-02-05
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： RAJARAM, Rajesh , PORTILLO BILBAO, Juan Enrique , YOU, Danning
IPC分类号： F23R3/10 , F23R3/46 , F23R3/54
CPC分类号： F23R3/26 , F23R3/10 , F23R3/46 , F23R3/54 , F23R2900/00014 , F23R2900/03043
摘要： A combustor assembly (10) in a gas turbine engine includes a liner (26) defining a combustion zone (28), at least one fuel injector (34, 36) for providing fuel, and a flow sleeve (20). An inner surface of the flow sleeve (20) defines an outer boundary for an air flow passageway (32). Upon the air reaching a head end (10A) of the combustor assembly (10) at an end of the air flow passageway (32) the air turns 180 degrees to flow into the combustion zone (28) where it is burned with the fuel. The combustor assembly (10) further includes an air inlet assembly (40) positioned radially between the liner (26) and the flow sleeve (20). The air inlet assembly (40) defines an inlet to the air flow passageway (32) and includes a plurality of overlapping conduits (42A-D) that are arranged such that the air entering the air flow passageway (32) passes through radial spaces between adjacent conduits (42A-D). The conduits (42A-D) may be arranged in an axially staggered pattern, may be angled in a direction away from the flow sleeve (20), and may be corrugated with peaks joining the adjacent conduits.
摘要翻译：燃气涡轮发动机中的燃烧器组件（10）包括限定燃烧区（28）的衬套（26），用于提供燃料的至少一个燃料喷射器（34,36）和流动套筒（20）。流动套管（20）的内表面限定了用于空气流动通道（32）的外部边界。当空气在空气流动通道（32）的一端到达燃烧器组件（10）的头端（10A）时，空气转动180度以流入燃烧区域（28），在那里燃料被燃烧。燃烧器组件（10）还包括径向位于衬套（26）和流动套管（20）之间的空气入口组件（40）。空气入口组件（40）限定了空气流动通道（32）的入口并且包括多个重叠的管道（42A-D），其布置成使得进入空气流动通道（32）的空气通过相邻导管（42A-D）。导管（42A-D）可以以轴向交错的图案布置，可以在远离流动套筒（20）的方向上成角度，并且可以是波纹状的，具有连接相邻导管的峰。

3. 发明申请

WO2017018983A1 COMBUSTOR SYSTEM AND METHOD FOR REDUCING COMBUSTION RESIDENCE TIME AND/OR DAMPING COMBUSTION DYNAMICS 审中-公开
标题翻译：用于减少燃烧停留时间和/或阻尼燃烧动力学的COMBUSTOR系统和方法
公开(公告)号：WO2017018983A1
公开(公告)日：2017-02-02
申请号：PCT/US2015/041952
申请日：2015-07-24
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： PORTILLO BILBAO, Juan Enrique , RAJARAM, Rajesh
IPC分类号： F23N5/24 , F23R3/44
CPC分类号： F23R3/44 , F23N5/247 , F23R2900/00014
摘要： Combustor system and method for reducing combustion residence time and/or damping combustion dynamics are provided. The system includes a first main burner (12) that in turn includes a first fluidic nozzle (16) tuned to convey a first flow of a fluid that oscillates at a first oscillation frequency to form a first flame (24). The combustor system further includes a second main burner (32) that in turn includes a second fluidic nozzle (34) tuned to convey a second flow of said fluid that oscillates at a second oscillation frequency to form a second flame (38). The first oscillation frequency and the second oscillation frequency have different values so that respective temporal characteristics of the first and second flames are different relative to one another. Flame-forming cups (22, 42) may be appropriately configured to impart different spatial characteristics to the first and second flames.
摘要翻译：提供了用于减少燃烧停留时间和/或阻尼燃烧动力学的燃烧器系统和方法。所述系统包括第一主燃烧器（12），所述第一主燃烧器（12）又包括第一流体喷嘴（16），所述第一流体喷嘴被调谐以传送以第一振荡频率振荡以形成第一火焰（24）的流体的第一流。燃烧器系统还包括第二主燃烧器（32），该第二主燃烧器（32）又包括第二流体喷嘴（34），该第二流体喷嘴被调谐以传送以第二振荡频率振荡以形成第二火焰（38）的所述流体的第二流。第一振荡频率和第二振荡频率具有不同的值，使得第一和第二火焰的相应时间特性彼此不同。火焰形成杯（22,42）可以适当地构造成赋予第一和第二火焰不同的空间特性。

4. 发明申请

WO2017018982A1 GAS TURBINE TRANSITION DUCT WITH LATE LEAN INJECTION HAVING REDUCED COMBUSTION RESIDENCE TIME 审中-公开
标题翻译：具有降低燃烧停留时间的轻度注射的气体涡轮转换管
公开(公告)号：WO2017018982A1
公开(公告)日：2017-02-02
申请号：PCT/US2015/041948
申请日：2015-07-24
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： LASTER, Walter Ray , PORTILLO BILBAO, Juan Enrique , FOX, Timothy A. , POWERS, Grant L.
IPC分类号： F23R3/42 , F23R3/06 , F23R3/28 , F23R3/34 , F23R3/46 , F01D9/02
CPC分类号： F01D9/023 , F23R3/06 , F23R3/286 , F23R3/346 , F23R3/425 , F23R3/46
摘要： An improved gas turbine combustion system having a reduced combustion residence time in a combustion turbine engine is provided. The combustion system includes a flow-accelerating structure (16, 51), such as a transition duct, having an inlet (26) and an outlet (28). The inlet (26) of the flow-accelerating structure () is fluidly coupled to receive a flow of combustion gases from a combustor outlet. At least one fuel injector (32, 64, 66) is disposed between the inlet (26) and the outlet (28) of the flow-accelerating structure (16, 51). The flow-accelerating structure (16, 51) causes an increasing speed to the flow of combustion gases, and, as a result, the flow of combustion gases in the flow-accelerating structure (16, 51) experiences a decreased static temperature and a reduced combustion residence time, each of which is effective to reduce NOx emissions at the high firing temperatures of the turbine engine.
摘要翻译：提供了一种在燃气轮机中具有减少的燃烧停留时间的改进的燃气轮机燃烧系统。燃烧系统包括具有入口（26）和出口（28）的流动加速结构（16,51），例如过渡管道。流动加速结构（）的入口（26）流体耦合以接收来自燃烧器出口的燃烧气体流。至少一个燃料喷射器（32,64,66）设置在流动加速结构（16,51）的入口（26）和出口（28）之间。流动加速结构（16,51）对燃烧气体的流动造成增加的速度，结果，流动加速结构（16,51）中的燃烧气体的流动经历降低的静态温度和减少的燃烧停留时间，其中每个都有效地减少在涡轮发动机的高燃烧温度下的NOx排放。

5. 发明申请

WO2016057009A1 COMBUSTOR AND METHOD FOR DAMPING VIBRATIONAL MODES UNDER HIGH-FREQUENCY COMBUSTION DYNAMICS 审中-公开
标题翻译：用于阻尼高频燃烧动力学振动模式的燃烧器和方法
公开(公告)号：WO2016057009A1
公开(公告)日：2016-04-14
申请号：PCT/US2014/059272
申请日：2014-10-06
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： PORTILLO BILBAO, Juan Enrique , RAJARAM, Rajesh , BECK, Christian , DEISS, Olga
IPC分类号： F23R3/00
CPC分类号： F23R3/60 , F23R3/002 , F23R2900/00014
摘要： A combustor and a method involving burner mains structurally configured to damp vibrational modes that can develop under high-frequency combustion dynamics are provided. The combustor may include a carrier (12), and a plurality of mains (16) disposed in the carrier. Some of the mains (labeled with the letter X) include a body having a different structural feature relative to the respective bodies of the remaining mains. The mains with the different structural feature may be selectively grouped in the carrier to form at least one set of such mains effective to damp predefined vibrational modes in the combustor.
摘要翻译：提供了一种燃烧器和一种涉及燃烧器主体的方法，其结构上被配置为阻止可在高频燃烧动态下发展的振动模式。燃烧器可以包括载体（12）和布置在载体中的多个主干（16）。一些电源（标有字母X）包括相对于剩余电源的相应主体具有不同结构特征的主体。具有不同结构特征的电源可以选择性地分组在载体中以形成至少一组这样的电源，以有效地阻止燃烧器中的预定义的振动模式。

6. 发明申请

WO2017034537A1 METHOD AND APPARATUS WITH ARRANGEMENT OF FUEL EJECTION ORIFICES CONFIGURED FOR MITIGATING COMBUSTION DYNAMICS IN A COMBUSTION TURBINE ENGINE 审中-公开
标题翻译：配置用于减少燃油涡轮发动机燃烧动力的燃油喷射装置的装置的方法和装置
公开(公告)号：WO2017034537A1
公开(公告)日：2017-03-02
申请号：PCT/US2015/046498
申请日：2015-08-24
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： PORTILLO BILBAO, Juan Enrique , RAJARAM, Rajesh , PRADE, Bernd , PENT, Jared M.
IPC分类号： F23R3/28 , F23D14/06 , F23D14/10
CPC分类号： F23R3/286 , F23R2900/00014
摘要： Apparatus and method for a combustion turbine engine are provided. A pre-mixing passage (24) has an upstream inlet arranged to receive a flow of air to be mixed with fuel. A fuel-injecting lance (12) is disposed in the pre-mixing passage. At least a first fuel ejection orifice (40) is disposed at a first axial location of the fuel-injecting lance. At least a second ejection orifice (42) is disposed at a second axial location of the fuel-injecting lance. A spacing between the first and second axial locations is arranged to effect oscillatory interference patterns in pockets comprising mixtures of air and fuel that flow towards a downstream outlet of the pre-mixing passage. The oscillatory interference patterns may be effective to promote homogeneity in the mixtures of air and fuel and dampen thermoacoustic oscillations in a flame (46) formed upon ignition of the mixtures of air and fuel.
摘要翻译：提供了一种用于燃气涡轮发动机的装置和方法。预混合通道（24）具有布置成接收与燃料混合的空气流的上游入口。燃料喷射喷枪（12）设置在预混合通道中。至少第一燃料喷射孔（40）设置在燃料喷射喷枪的第一轴向位置处。至少第二喷射孔（42）设置在燃料喷射喷枪的第二轴向位置处。第一和第二轴向位置之间的间隔布置成在包含空气和燃料的混合物的腔中产生振动干涉图案，该混合物流向预混合通道的下游出口。振荡干涉图案可以有效地促进空气和燃料的混合物中的均匀性并且抑制在空气和燃料的混合物点燃时形成的火焰（46）中的热声振荡。

7. 发明申请

WO2016085494A1 FUEL LANCE WITH MEANS FOR INTERACTING WITH A FLOW OF AIR AND IMPROVE BREAKAGE OF AN EJECTED LIQUID JET OF FUEL 审中-公开
标题翻译：用于与空气流相互交换并改善喷射的液体喷射器的燃料的燃料
公开(公告)号：WO2016085494A1
公开(公告)日：2016-06-02
申请号：PCT/US2014/067620
申请日：2014-11-26
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： PORTILLO BILBAO, Juan Enrique
IPC分类号： F23R3/28 , F23D11/38
CPC分类号： F23R3/286 , F02C7/222 , F23D11/38 , F23D2900/11001
摘要： Apparatus and method for a combustion turbine engine are provided. The apparatus includes a fuel-injecting lance (12) to convey a liquid fuel to a downstream end (16) ofthe lance. At least onejet in cross- flow injector (18) may be disposed at the downstream end ofthe lance, and includes an ejection orifice (20) responsive to eject a liquid jet (22) of the fuel. A plurality of surface irregularities (28, 29, 30, 50, 52, 54) is disposed at least on a portion of a wall (32) of the fuel-injecting lance exposed to the flow of air and proximate to the ejection orifice (20). The plurality of surface irregularities be arranged to interact (e.g., turbulent interaction) with the flow of air to promote breakage of the ejected liquid jet of fuel compared to an injector lacking such surface irregularities.
摘要翻译：提供了一种用于燃气涡轮发动机的装置和方法。该装置包括用于将液体燃料输送到喷枪的下游端（16）的燃料喷射喷枪（12）。横流喷射器（18）中的至少一个喷射器可以设置在喷枪的下游端，并且包括响应于喷射燃料的液体喷射（22）的喷射孔（20）。多个表面凹凸（28,29,30,52,52,54）至少设置在暴露于空气流并靠近喷射孔的燃料喷射喷枪的壁（32）的至少一部分上 20）。多个表面凹凸布置成与空气流相互作用（例如湍流相互作用），以促进与不存在这种表面不规则的注射器相比喷射的液体燃料喷射液的破裂。

8. 发明申请

WO2015016995A3 ACOUSTIC DAMPING SYSTEM FOR A COMBUSTOR OF A GAS TURBINE ENGINE 审中-公开
公开(公告)号：WO2015016995A3
公开(公告)日：2015-02-05
申请号：PCT/US2014/036820
申请日：2014-05-05
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： PORTILLO BILBAO, Juan Enrique , RAJARAM, Rajesh , YOU, Danning , SPENCE, Kevin J.
IPC分类号： F23R3/00 , F23R3/60
摘要： An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (14) is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) positioned within the gas turbine engine combustor (12) at an outer housing (18) forming a combustor basket (22) and extending circumferentially within the combustor (12). The resonator (16) may be positioned in a head region (20) of the combustor basket (22). In one embodiment, the resonator (16) may be positioned in close proximity to an intersection (24) between the outer housing (18) and an upstream wall (26) defining at least a portion of the combustor (12). The acoustic damping resonator system (14) may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions

9. 发明申请

WO2020086069A1 TRANSITION DUCT SYSTEM WITH NON-METALLIC THERMALLY-INSULATING LINERS SUPPORTED WITH SPLITTABLE METALLIC SHELL STRUCTURES FOR DELIVERING HOT-TEMPERATURE GASSES IN A COMBUSTION TURBINE ENGINE 审中-公开
公开(公告)号：WO2020086069A1
公开(公告)日：2020-04-30
申请号：PCT/US2018/057231
申请日：2018-10-24
申请人： SIEMENS ENERGY, INC.
发明人： PORTILLO BILBAO, Juan Enrique , MORRISON, Jay A. , SHIPPER, Jonathan E., Jr. , SMITH, Kyle , WALL, Andrew
IPC分类号： F01D9/02 , F01D5/28
摘要： A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. A non-metallic thermally-insulating liner (22), as may be made from a ceramic-based material, such as a ceramic matrix composite (CMC) material or other high-temperature ceramic-based material, e.g., a MAX phase material, may be inwardly disposed onto a splittable or otherwise separable metallic shell support structure (38). Disclosed structural arrangements are effective to securely attach the non-metallic thermally-insulating liner in the presence of substantial flow path pressurization. Cost-effective serviceability of the transition duct systems is realizable since the liner can be readily removed and replaced as needed.

10. 发明申请

WO2015148751A1 GAS TURBINE ENGINE HAVING A DUAL OUTLET FUEL-PREMIX-NOZZLE FOR A SECONDARY COMBUSTOR STAGE 审中-公开
标题翻译：燃气涡轮发动机有一个双出口燃油喷嘴用于二次燃烧器阶段
公开(公告)号：WO2015148751A1
公开(公告)日：2015-10-01
申请号：PCT/US2015/022629
申请日：2015-03-26
申请人： SIEMENS ENERGY, INC.
发明人： LASTER, Walter Ray , MARTIN, Scott M. , PORTILLO BILBAO, Juan Enrique , HARDES, Jacob , FOX, Timothy A.
IPC分类号： F23R3/06 , F23R3/16 , F23R3/28 , F23R3/34
CPC分类号： F23R3/346 , F23R3/06 , F23R3/16 , F23R3/286
摘要： A secondary fuel stage (14) of a combustor of a gas turbine engine. The combustor has a main combustion zone upstream of the secondary fuel stage to ignite working gas. The secondary fuel stage includes a nozzle (18) with dual outlets (20, 22) oriented with a circumferential component to inject an air-fuel mixture into the combustor. The nozzle is effective to entrain the air-fuel mixture with the working gas such that a peak temperature of the working gas at a location downstream of the secondary fuel stage is less than a peak temperature of working gas if the air-fuel mixture were injected into the combustor with a single outlet nozzle.
摘要翻译：燃气涡轮发动机的燃烧器的二次燃料级（14）。燃烧器具有在二级燃料级上游的主燃烧区，以点燃工作气体。辅助燃料级包括具有双向出口（20,22）的喷嘴（18），其具有定向成周向部件以将空气 - 燃料混合物喷射到燃烧器中。该喷嘴有效地将空气 - 燃料混合物与工作气体夹带，使得如果空气 - 燃料混合物被注入，则在次级燃料级下游的工作气体的峰值温度小于工作气体的峰值温度使用单个出口喷嘴进入燃烧器。

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