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1. 发明申请

WO2014123970A1 COMBUSTOR LINER FOR A CAN-ANNULAR GAS TURBINE ENGINE AND A METHOD FOR CONSTRUCTING SUCH A LINER 审中-公开
标题翻译：用于CAN-ANNULAR气体涡轮发动机的燃烧器衬管和用于构造这种衬管的方法
公开(公告)号：WO2014123970A1
公开(公告)日：2014-08-14
申请号：PCT/US2014/014817
申请日：2014-02-05
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： CAI, Weidong , MIDUTURI, Krishna C. , RITLAND, David M.
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F23R3/005 , F23R2900/03043 , F23R2900/03045 , Y10T29/49229
摘要： A combustor liner (30) for a can-annular gas turbine engine (10) and a method for constructing such a liner are provided. The combustor liner includes an annular wall member (32). A cooling channel (34, 42, 50, 54, 56, 58) is formed through the wall member and extends from an inlet end of the liner to an outlet end of the liner. A property of the cooling channel may be varied along a length of the cooling channel. The cooling channel may be formed through the combustor liner using an electro-chemical machining (ECM) process or a three dimensional printing process (3DP).
摘要翻译：提供了一种用于罐环式燃气涡轮发动机（10）的燃烧器衬套（30）和用于构造这种衬套的方法。燃烧器衬套包括环形壁构件（32）。冷却通道（34,42,50,54,56,58）穿过壁件形成，并从衬套的入口端延伸到衬套的出口端。冷却通道的特性可以沿冷却通道的长度变化。冷却通道可以使用电化学加工（ECM）工艺或三维印刷工艺（3DP）通过燃烧器衬套形成。

2. 发明申请

WO2020050854A1 ANGULAR COOLING CHANNELS FOR IMPROVED MECHANICAL LIFE 审中-公开
公开(公告)号：WO2020050854A1
公开(公告)日：2020-03-12
申请号：PCT/US2018/049952
申请日：2018-09-07
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MIDUTURI, Krishna C. , TULLY, Landon , TERDALKAR, Sachin , KRISHNAN, Vaidyanathan , DAVE, Urmi B. , WHIPP, Heather Marie
IPC分类号： F01D9/02 , F23R3/08
摘要： An angular cooling arrangement to provide increased mechanical life is presented. The cooling arrangement includes a cooling channel disposed in a combustor liner (28) adapted to provide a region of blocking flow within a combustor exit/transition inlet ring interface (22). The cooling arrangement includes a cooling channel (26) and a redirecting element (30) that guides cooling fluid exiting the cooling channels that substantially reduces the tendency of hot working fluids to flow upstream away from a recirculation zone (42) within the combustor exit/transition inlet ring interface (22). With the presented arrangement, the need for purge air in this region is reduced, cooling efficiency is increased, NOx emissions are controlled to acceptable levels, and component life targets are met.

3. 发明申请

WO2015100081A1 A CONTROL SYSTEM AND METHOD FOR CONTROLLING A GAS TURBINE ENGINE DURING TRANSIENTS 审中-公开
标题翻译：用于在瞬态过程中控制气体涡轮发动机的控制系统和方法
公开(公告)号：WO2015100081A1
公开(公告)日：2015-07-02
申请号：PCT/US2014/070715
申请日：2014-12-17
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MIDUTURI, Krishna C. , KOZACHUK, Danny W.
IPC分类号： F02C9/22 , F02C9/28 , F02C9/54
CPC分类号： F02C9/54 , F02C9/28 , F02D41/30 , F05D2270/04 , F05D2270/303 , Y02T10/42
摘要： A control system and method for a gas turbine engine are provided. A controller (40) is responsive to at least one parameter to control an air-to-fuel ratio. The parameter may be a measured engine exhaust temperature from a temperature sensor (42). During a transient, such as a ramping condition of the engine, a measured value of such parameter may have a time lag affecting one or more control settings during the transient condition. The controller is programmed to predictively determine a bias for the measured value of the parameter to correct such control settings and avoid combustion instabilities and high emissions during such transient conditions.
摘要翻译：提供了一种用于燃气涡轮发动机的控制系统和方法。控制器（40）响应于至少一个参数来控制空燃比。该参数可以是来自温度传感器（42）的测量的发动机排气温度。在诸如发动机的斜坡状态的瞬变期间，这种参数的测量值可能在瞬态条件下具有影响一个或多个控制设置的时间延迟。控制器被编程为预测性地确定参数的测量值的偏差，以校正这种控制设置，并避免在这种瞬态条件下的燃烧不稳定性和高排放。

4. 发明申请

WO2017052547A1 DUAL STAGE VANE PILOT NOZZLE 审中-公开
标题翻译：双级风向导喷嘴
公开(公告)号：WO2017052547A1
公开(公告)日：2017-03-30
申请号：PCT/US2015/051884
申请日：2015-09-24
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： BERTONCELLO, James , MIDUTURI, Krishna C. , RITLAND, David M , ZURHORST, Marcus , WEGNER, Bernhard , HUTH, Michael
IPC分类号： F23R3/28 , F23R3/14 , F23C7/00
CPC分类号： F23R3/286 , F23C7/004 , F23C2900/07001 , F23D2900/11402 , F23R3/14
摘要： A dual stage vane pilot nozzle (100) has a non-diffusion nozzle (110) and a first fuel stage (121) and a second fuel stage (122). The first fuel stage (121) has a first fuel injector (101) having first injection holes (103) and a first fuel annulus (105). The second fuel stage (122) has a second fuel injector (102) having second injection holes (104) and a second fuel annulus (106). The non-diffusion (110) does not have a diffusion tip. This arrangement allows for the reduction of nitrogen oxide emissions.
摘要翻译：双级叶片先导喷嘴（100）具有非扩散喷嘴（110）和第一燃料级（121）和第二燃料级（122）。第一燃料台（121）具有第一燃料喷射器（101），其具有第一喷射孔（103）和第一燃料环（105）。第二燃料台（122）具有第二燃料喷射器（102），其具有第二喷射孔（104）和第二燃料环（106）。非扩散（110）不具有扩散尖端。这种布置允许减少氮氧化物排放。

5. 发明申请

WO2014197219A1 ASYMMETRIC BASE PLATE COOLING WITH ALTERNATING SWIRL MAIN BURNERS 审中-公开
标题翻译：不对称基板冷却与替代SWIRL主燃烧器
公开(公告)号：WO2014197219A1
公开(公告)日：2014-12-11
申请号：PCT/US2014/039260
申请日：2014-05-23
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MIDUTURI, Krishna C. , RITLAND, David M.
IPC分类号： F23R3/04 , F23R3/28 , F23R3/06
CPC分类号： F23R3/16 , F23R3/005 , F23R3/04 , F23R3/12 , F23R3/283 , F23R3/286 , F23R2900/03041 , F23R2900/03042
摘要： A combustor arrangement (10) including: a pilot burner (22) having a pilot cone (62); a plurality of clockwise (130) main swirlers interposed among a plurality of counterclockwise (132) main swirlers and disposed concentrically about the pilot burner; and a base plate (40) transverse to the main swirlers. Inbound-zones (134) exist where adjacent portions (106) of adjacent flows (108) through main swirlers flow toward the pilot cone, and interposed between the inbound zones outbound zones (136) exist where adjacent portions of adjacent flows flow away from the pilot cone. The arrangement is configured to preferentially deliver more cooling fluid to the inbound zones than the outbound zones.
摘要翻译：一种燃烧器装置（10），包括：具有先导锥体（62）的引燃燃烧器（22）; 多个顺时针（130）主旋流器插入在多个逆时针（132）主旋流器中并且围绕引燃燃烧器同心地设置; 和横向于主旋流器的基板（40）。存在入口区（134），其中通过主旋流器的相邻流（108）的相邻部分（106）朝向先导锥流动，并且介于入射区出射区（136）之间，其中相邻流的相邻部分离开先导锥该布置被配置为优先地向出入区域输送更多的冷却流体到出站区域。

6. 发明申请

WO2018056994A1 ATOMIZER FUEL NOZZLE FOR OIL OPERATION IN A TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机中用于油操作的雾化器燃料喷嘴
公开(公告)号：WO2018056994A1
公开(公告)日：2018-03-29
申请号：PCT/US2016/053231
申请日：2016-09-23
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： RAMIER, Stephen A. , MIDUTURI, Krishna C. , ABOU-JAOUDE, Khalil Farid
IPC分类号： F23R3/36 , F23L7/00 , F23D11/10 , F23D17/00
CPC分类号： F23R3/36 , F23D11/108 , F23D17/002 , F23L7/002
摘要： A turbine engine can have an atomizer having two orifices that form an intersecting spray cone. The turbine engine can also have an atomizer that has three orifices that forms a partially filled spray cone. The intersecting sprays cones or the partially filled spray cone permits operation of the turbine engine without water. The intersecting spray cones or partially filled spray cone can also be used to facilitate ignition and lower NOx emissions.
摘要翻译：涡轮发动机可以具有雾化器，雾化器具有形成交叉喷雾锥的两个孔口。涡轮发动机也可以具有雾化器，该雾化器具有形成部分填充的喷雾锥的三个孔。相交的喷雾锥体或部分填充的喷雾锥体允许涡轮发动机在没有水的情况下运行。相交的喷雾锥体或部分填充的喷雾锥体也可用于促进点火和降低NOx排放。

7. 发明申请

WO2018063151A1 FUEL OIL AXIAL STAGE COMBUSTION FOR IMPROVED TURBINE COMBUSTOR PERFORMANCE 审中-公开
标题翻译：燃料油轴向燃烧改善了汽轮机燃烧器的性能
公开(公告)号：WO2018063151A1
公开(公告)日：2018-04-05
申请号：PCT/US2016/053912
申请日：2016-09-27
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： MIDUTURI, Krishna C. , RAMIER, Stephen A. , LASTER, Walter Ray
IPC分类号： F23R3/34 , F23R3/04
摘要： A turbine engine has two combustion zones so as to operate in conditions where water scarcity is an issue. The secondary combustion zone is located downstream of the primary combustion zone. Fuel can be fed into an air scoop having air from a shell surrounding the primary and secondary combustion zone. The feeding of the fuel through the air scoop allows atomization of the fuel. The mixture can then enter the secondary combustion zone and mix with the products from the first combustion zone.
摘要翻译：涡轮发动机具有两个燃烧区域，以便在水资源匮乏成为问题的情况下运行。二次燃烧区位于主燃烧区的下游。燃料可以从围绕主燃烧区和次燃烧区的壳体供给到具有空气的空气铲中。通过空气铲进入燃料允许雾化燃料。混合物然后可以进入二次燃烧区并与来自第一燃烧区的产物混合。

8. 发明申请

WO2017196356A1 A METHOD OF SELECTIVE COMBUSTOR CONTROL FOR REDUCED EMISSIONS 审中-公开
标题翻译：一种减少排放的选择性COMBUSTOR控制方法
公开(公告)号：WO2017196356A1
公开(公告)日：2017-11-16
申请号：PCT/US2016/032201
申请日：2016-05-12
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： JOHNSON, Clifford E. , CAI, Weidong , MIDUTURI, Krishna C. , KARANJA, Ben , HUTH, Michael , KREBS, Werner , SEIFARTH, Mark , PRIMKE, Thomas , GHERMAY, Yohannes
IPC分类号： F23R3/34 , F23R3/46 , F23R3/28 , F02C7/228
摘要： A method, including: operating an industrial gas turbine engine having a plurality of combustor cans (100) arranged in an annular array, each can having burner stages (122, 124, 132) and a pilot burner arrangement (104) having a premix pilot burner (108) and a diffusion pilot burner (106); operating in asymmetric combustion, wherein at least one can is a warm can where respective burners stages are off and remaining cans operate as hot cans where respective burner stages are on; and while maintaining a constant rate of fuel flow to the pilot burner arrangement of the warm can, changing fuel fractions within the pilot burner arrangement of the warm can.
摘要翻译：一种方法，所述方法包括：操作工业燃气涡轮发动机，所述工业燃气涡轮发动机具有布置成环形阵列的多个燃烧器罐（100），每个燃料罐具有燃烧器级（122,124,132）和引燃器具有预混合引燃燃烧器（108）和扩散引燃燃烧器（106）的装置（104）; 在不对称燃烧中操作，其中至少一个罐是热罐，其中各个燃烧器级关闭，并且剩余罐作为各个燃烧器级开启时的热罐运行; 同时保持恒温燃料流量流向暖罐的引燃器装置，改变暖罐引燃器装置内的燃料馏分。

9. 发明申请

WO2015073215A1 FUEL INJECTION SYSTEM FOR A TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机燃油喷射系统
公开(公告)号：WO2015073215A1
公开(公告)日：2015-05-21
申请号：PCT/US2014/063065
申请日：2014-10-30
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： MIDUTURI, Krishna C. , WASIF, Samer P.
IPC分类号： F23R3/28 , F23R3/34
CPC分类号： F23R3/286 , F23R3/346
摘要： A fuel system (10) for a turbine engine (12) for improving efficiency in a fuel system (10) where a major stage (14) and secondary stage (16) can be combined and held to a relatively constant fuel ratio while maintaining acceptable engine dynamics and NOx emissions is disclosed. The fuel system (10) may be formed from a first premix injector assembly stage (18) positioned upstream from a combustor basket (20), whereby the first premix injector assembly stage (18) is a secondary injector system. The fuel system (10) may be formed from a first primary injector assembly stage (22), which is a main injector system, positioned downstream from the first premix injector assembly stage (18). The first premix injector assembly stage (18) and the first primary injector assembly stage (22) may be coupled together such that the fuel system (10) is capable of emitting fuel into a combustor (24) of the turbine engine (12) via the first premix injector assembly stage (18) and the first primary injector assembly stage (22) simultaneously.
摘要翻译：一种用于提高燃料系统（10）的效率的涡轮发动机（12）的燃料系统（10），其中主级（14）和第二级（16）可以组合并保持为相对恒定的燃料比，同时保持可接受公开了发动机动力学和NOx排放。燃料系统（10）可以由位于燃烧器筐（20）的上游的第一预混合喷射器组件平台（18）形成，由此第一预混合喷射器组件平台（18）是二次喷射器系统。燃料系统（10）可以由位于第一预混合喷射器组件平台（18）下游的主喷射器系统的第一主喷射器组件台（22）形成。第一预混合喷射器组件平台（18）和第一主要喷射器组件平台（22）可以联接在一起，使得燃料系统（10）能够经由气体发动机（12）的燃烧器（24）经由第一预混注射器组件级（18）和第一主注射器组件级（22）。

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