专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

WO2013122643A2 DEVICE TO LOWER NOX IN A GAS TURBINE ENGINE COMBUSTION SYSTEM 审中-公开
标题翻译：在燃气涡轮发动机燃烧系统中降低NOx的装置
公开(公告)号：WO2013122643A2
公开(公告)日：2013-08-22
申请号：PCT/US2012/066590
申请日：2012-11-27
申请人： SIEMENS ENERGY, INC. , LASTER, Walter R. , SCHILP, Reinhard , WIEBE, David J.
发明人： LASTER, Walter R. , SCHILP, Reinhard , WIEBE, David J.
IPC分类号： F23C9/08
CPC分类号： F23R3/42 , F23C9/08 , F23R3/26
摘要： An emissions control system for a gas turbine engine including a flow-directing structure (24) that delivers combustion gases (22) from a burner (32) to a turbine. The emissions control system includes: a conduit (48) configured to establish fluid communication between compressed air (22) and the combustion gases within the flow-directing structure (24). The compressed air (22) is disposed at a location upstream of a combustor head-end and exhibits an intermediate static pressure less than a static pressure of the combustion gases within the combustor (14). During operation of the gas turbine engine a pressure difference between the intermediate static pressure and a static pressure of the combustion gases within the flow-directing structure (24) is effective to generate a fluid flow through the conduit (48).
摘要翻译：一种用于燃气涡轮发动机的排放控制系统，其包括将燃烧气体（22）从燃烧器（32）输送到涡轮机的流动引导结构（24）。排放物控制系统包括：导管（48），其配置成建立压缩空气（22）与导流结构（24）内的燃烧气体之间的流体连通。压缩空气（22）设置在燃烧器头端的上游位置处，并且具有小于燃烧器（14）内的燃烧气体的静压的中间静压力。在燃气涡轮发动机的操作期间，导流结构（24）内的中间静压与燃烧气体的静压之间的压力差有效地产生通过导管（48）的流体流。

2. 发明申请

WO2014110385A1 LEAN-RICH AXIAL STAGE COMBUSTION IN A CAN-ANNULAR GAS TURBINE ENGINE 审中-公开
标题翻译：在CAN-ANNULAR气体涡轮发动机中的精益求精的轴向燃烧
公开(公告)号：WO2014110385A1
公开(公告)日：2014-07-17
申请号：PCT/US2014/011065
申请日：2014-01-10
申请人： SIEMENS ENERGY, INC.
发明人： LASTER, Walter R. , SZEDLACSEK, Peter
IPC分类号： F23R3/28 , F23R3/34
CPC分类号： F23R3/346 , F23R3/286
摘要： An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16). The gas turbine (10) also includes a fuel manifold (28) to extend along the outer surface (20) of the combustor extender (16), with fuel nozzles (30) to align with the respective openings (18). A method for axial stage combustion in the gas turbine engine (10) is also presented.
摘要翻译：一种用于燃气涡轮发动机（10）中的贫/富燃烧的装置和方法，其包括燃烧器（12），过渡部（14）和燃烧器延长器（16），其位于燃烧器（12）和过渡（14）将燃烧器（12）连接到过渡部（14）。开口（18）沿着燃烧器延长器（16）的外表面（20）形成。燃气涡轮（10）还包括燃料歧管（28），其沿着燃烧器延长器（16）的外表面（20）延伸，燃料喷嘴（30）与相应的开口（18）对齐。还提出了一种用于燃气涡轮发动机（10）中的轴向级燃烧的方法。

3. 发明申请

WO2015199690A1 AXIAL STAGE COMBUSTION SYSTEM WITH EXHAUST GAS RECIRCULATION 审中-公开
标题翻译：具有排气回收的轴流式燃烧系统
公开(公告)号：WO2015199690A1
公开(公告)日：2015-12-30
申请号：PCT/US2014/044241
申请日：2014-06-26
申请人： SIEMENS ENERGY, INC.
发明人： MARTIN, Scott M. , LASTER, Walter R. , PORTILLO BILBAO, Juan Enrique
IPC分类号： F23R3/34 , F23C9/08 , F02C3/34 , F23R3/28
CPC分类号： F02C3/34 , F01K23/10 , F02C3/14 , F02C7/22 , F05D2220/60 , F05D2220/76 , F05D2240/35 , F23C9/08 , F23C2201/30 , F23C2202/20 , F23R3/286 , F23R3/346 , Y02E20/16
摘要： A method of operating an axial stage combustion system in a gas turbine engine (12) including an EGR system (14) that extracts a portion of exhaust gas produced by the gas turbine engine (12) to a second axial stage of a combustor (18). The extracted exhaust gas is provided at an elevated temperature to a group of injector nozzles (50) at the second axial stage (34) of the combustor (18). A secondary fuel supply line (34) extends to an inlet on each of the injector nozzles (50), and the fuel is mixed with the exhaust gas within the injector nozzles (50) and the mixture of fuel and exhaust gas is injected into the second axial stage (34) of the combustor (18).
摘要翻译：一种在包括EGR系统（14）的燃气涡轮发动机（12）中操作轴向级燃烧系统的方法，该EGR系统将由燃气涡轮发动机（12）产生的废气的一部分提取到燃烧器（18）的第二轴向级）。提取的废气在升高的温度下被设置在燃烧器（18）的第二轴向级（34）处的一组喷射器喷嘴（50）。辅助燃料供给管线（34）延伸到每个喷射器喷嘴（50）上的入口，并且燃料与喷射器喷嘴（50）内的废气混合，燃料和废气的混合物被注入燃烧器（18）的第二轴向级（34）。

4. 发明申请

WO2015094814A1 AXIAL STAGE INJECTION DUAL FREQUENCY RESONATOR FOR A COMBUSTOR OF A GAS TURBINE ENGINE 审中-公开
标题翻译：气动涡轮发动机燃烧器的轴向注射双频谐振器
公开(公告)号：WO2015094814A1
公开(公告)日：2015-06-25
申请号：PCT/US2014/069317
申请日：2014-12-09
申请人： SIEMENS ENERGY, INC.
发明人： PENT, Jared M. , PORTILLO BILBAO, Juan Enrique , JOHNSON, Perry L. , ABU-IRSHAID, Esam , LASTER, Walter R. , MARTIN, Scott M. , ROFAIL, Rafik N.
IPC分类号： F23R3/04 , F23R3/24 , F23R3/46
CPC分类号： F23R3/16 , F23R3/045 , F23R3/34 , F23R3/46 , F23R2900/00014
摘要： A gas turbine engine (202) including a secondary fuel stage (218) which also functions as a dual frequency resonator. The engine includes a combustor (210) and a casing (205) enclosing the combustor to define a volume (214). The secondary fuel stage includes a nozzle (217) sized to be effective as a transverse resonator at a high frequency. The nozzle and the volume (214) of the casing are sized to be effective as a longitudinal resonator at an intermediate frequency.
摘要翻译：一种燃气涡轮发动机（202），其包括也用作双频谐振器的二次燃料级（218）。发动机包括燃烧器（210）和封闭燃烧器以限定容积（214）的壳体（205）。二次燃料级包括尺寸适于以高频有效的横向谐振器的喷嘴（217）。壳体的喷嘴和体积（214）的尺寸被确定为在中频处作为纵向谐振器有效。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式