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1. 发明申请

US20130180255A1 RATIONAL LATE LEAN INJECTION 有权
标题翻译： RALY LATE LEAN INJECTION
公开(公告)号：US20130180255A1
公开(公告)日：2013-07-18
申请号：US13349923
申请日：2012-01-13
申请人： Borys Borysovich Shershnyov , Leonid Yul'evich Ginesin , Krishnakumar Venkataraman
发明人： Borys Borysovich Shershnyov , Leonid Yul'evich Ginesin , Krishnakumar Venkataraman
IPC分类号： F02C7/22
CPC分类号： F23R3/005 , F23R3/286 , F23R3/346 , F23R2900/00017
摘要： A combustor section of a gas turbine includes a combustor liner, a sleeve and a fuel-air mixing tube. The combustor liner defines a combustion chamber. The sleeve surrounds the combustor liner. The combustor liner and the sleeve define an annular flow space. The fuel-air mixing tube is configured to channel a mixture of fuel and air and includes an inlet and an outlet. The inlet is in fluid communication with an exterior of the sleeve, and the outlet is in fluid communication with the combustion chamber. The combustor casing encloses the combustor section upstream relative to the inlet of the mixing tube and extends downstream. The sleeve and the combustor casing define a discharge air space. The discharge space is in fluid communication with the mixing tube. The fuel supplying device is located exteriorly of the combustor casing and is configured to inject fuel into the mixing tube.
摘要翻译：燃气轮机的燃烧器部分包括燃烧器衬套，套管和燃料 - 空气混合管。燃烧器衬套限定燃烧室。套筒围绕燃烧器衬套。燃烧器衬套和套管限定环形流动空间。燃料 - 空气混合管构造成引导燃料和空气的混合物并且包括入口和出口。入口与套筒的外部流体连通，并且出口与燃烧室流体连通。燃烧器壳体相对于混合管的入口将燃烧器部分包围在上游并在下游延伸。套筒和燃烧器壳体限定排放空气空间。放电空间与混合管流体连通。燃料供给装置位于燃烧器壳体的外部，并且被配置为将燃料喷射到混合管中。

2. 发明授权

US09500372B2 Multi-zone combustor 有权
标题翻译：多区域燃烧器
公开(公告)号：US09500372B2
公开(公告)日：2016-11-22
申请号：US13983936
申请日：2011-12-05
申请人： Leonid Yulevich Ginesin , Borys Borysovich Shershnyov , Andrey Pavlovich Subbota , Almaz Kamilevich Valeev
发明人： Leonid Yulevich Ginesin , Borys Borysovich Shershnyov , Andrey Pavlovich Subbota , Almaz Kamilevich Valeev
IPC分类号： F23R3/34 , F23R3/28 , F23R3/14 , F23R3/54
CPC分类号： F23R3/34 , F23R3/286 , F23R3/346 , F23R3/54
摘要： A multi-zone combustor is provided and includes a pre-mixer configured to output a first mixture to a primary zone of a combustor section and a stepped center body disposable in an annulus defined within the pre-mixer. The stepped center body includes an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section.
摘要翻译：提供了多区域燃烧器，其包括预混合器，该预混合器构造成将第一混合物输出到燃烧器部分的主区域和一次性地在预混合器内限定的环形空间内的阶梯式中心体。阶梯式中心体包括外主体，其被构造成在第一径向和轴向台阶处输出第二混合物到燃烧器部分的次级区域，以及内部主体，该内部主体一次性地被限定在外部主体内的环形空间中，并被配置为在第二径向并且轴向步骤将第三混合物连接到所述燃烧器部分的第三区域。

3. 发明申请

US20170261209A9 ANTI-COKING LIQUID FUEL INJECTOR ASSEMBLY FOR A COMBUSTOR 有权
公开(公告)号：US20170261209A9
公开(公告)日：2017-09-14
申请号：US14082677
申请日：2013-11-18
申请人： Leonid Yulievich GINESSIN , Borys Borysovich SHERSHNYOV
发明人： Leonid Yulievich GINESSIN , Borys Borysovich SHERSHNYOV
IPC分类号： F23R3/28
CPC分类号： F23R3/286 , F05D2250/25 , F23D11/107 , F23R3/28 , F23R3/283 , F23R3/343 , F23R3/36 , F23R2900/00004
摘要： A liquid fuel cartridge assembly for a gas turbine combustor comprising an elongated stem provided with a fuel injector tip at an aft end of said stem, said injector tip provided with a pilot fuel passage extending to a pilot fuel orifice; a plurality of air channels surrounding said pilot fuel passage and in communication with plural air holes; an annular main fuel passage surrounding said plurality of air channels and in communication with plural fuel exit holes; and a plurality of substantially radially oriented air supply holes in said stem upstream but proximate to a forward end of said tip in communication with said plurality of air channels.

4. 发明申请

US20140345289A1 GAS TURBOMACHINE COMBUSTOR ASSEMBLY INCLUDING A LIQUID FUEL START-UP SYSTEM 审中-公开
标题翻译：气体涡轮搅拌机总成包括液体燃料启动系统
公开(公告)号：US20140345289A1
公开(公告)日：2014-11-27
申请号：US13984923
申请日：2012-02-01
申请人： Borys Borysovich Shershnyov
发明人： Borys Borysovich Shershnyov
IPC分类号： F02C9/40 , F23K5/12 , F23R3/36
CPC分类号： F02C9/40 , F23D11/22 , F23D2900/00014 , F23K5/002 , F23K5/10 , F23K5/12 , F23K2301/103 , F23K2400/00 , F23K2900/05004 , F23R3/343 , F23R3/36
摘要： A turbomachine combustor assembly includes a combustor body, a combustion chamber defined within the combustor body, one or more combustion nozzles positioned to direct a combustible fluid into the combustion chamber, and a fuel start-up system fluidly connected to the combustion chamber. The fuel start-up system is configured and disposed to combine a liquid fuel and a combustible gas to form an ignition fuel. A pilot nozzle is fluidly connected to the fuel start-up system. The pilot nozzle is configured and disposed to deliver an atomized cloud of the ignition fuel toward the combustion chamber.
摘要翻译：涡轮机械燃烧器组件包括燃烧器主体，限定在燃烧器主体内的燃烧室，定位成将可燃流体引导到燃烧室中的一个或多个燃烧喷嘴以及流体连接到燃烧室的燃料起动系统。燃料启动系统被构造和布置成组合液体燃料和可燃气体以形成点火燃料。导向喷嘴流体地连接到燃料起动系统。引导喷嘴被配置和设置成将点火燃料的雾化云传递到燃烧室。

5. 发明申请

US20140260259A1 MULTI-ZONE COMBUSTOR 有权
标题翻译：多区域协调员
公开(公告)号：US20140260259A1
公开(公告)日：2014-09-18
申请号：US13983936
申请日：2011-12-05
申请人： Leonid Yulevich Ginesin , Borys Borysovich Shershnyov , Andrey Pavlovich Subbota , Almaz Kamilevich Valeev
发明人： Leonid Yulevich Ginesin , Borys Borysovich Shershnyov , Andrey Pavlovich Subbota , Almaz Kamilevich Valeev
IPC分类号： F23R3/34 , F23R3/28
CPC分类号： F23R3/34 , F23R3/286 , F23R3/346 , F23R3/54
摘要： A multi-zone combustor is provided and includes a pre-mixer configured to output a first mixture to a primary zone of a combustor section and a stepped center body disposable in an annulus defined within the pre-mixer. The stepped center body includes an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section.
摘要翻译：提供了多区域燃烧器，其包括预混合器，该预混合器构造成将第一混合物输出到燃烧器部分的主区域和一次性地在预混合器内限定的环形空间内的阶梯式中心体。阶梯式中心体包括外主体，其被构造成在第一径向和轴向台阶处输出第二混合物到燃烧器部分的次级区域，以及内部主体，该内部主体一次性地被限定在外部主体内的环形空间中，并被配置为在第二径向并且轴向步骤将第三混合物连接到所述燃烧器部分的第三区域。

6. 发明申请

US20140123671A1 COMBUSTOR AND METHOD OF SUPPLYING FUEL TO THE COMBUSTOR 有权
标题翻译：燃料和燃料供应给燃烧器的方法
公开(公告)号：US20140123671A1
公开(公告)日：2014-05-08
申请号：US14122694
申请日：2011-06-30
申请人： Borys Borysovich Shershnyov , Geoffrey David Myers , Leonid Yulyevich Ginesin
发明人： Borys Borysovich Shershnyov , Geoffrey David Myers , Leonid Yulyevich Ginesin
IPC分类号： F23R3/28 , F23R3/14 , F23R3/34
CPC分类号： F23R3/286 , F23R3/14 , F23R3/34 , F23R3/343 , F23R3/54
摘要： A combustor (10) includes a liner (12) that defines a combustion chamber (18) first pre-mix chamber (14) is upstream of the combustion chamber, and a fuel plenum (40) in fluid communication with the first pre-mix chamber surrounds a least a portion of the first pre-mix chamber. A method of supplying a fuel to combustor includes flowing the fuel over an outer surface of a first pre-mix chamber and into the first pre-mix chamber.
摘要翻译：燃烧器（10）包括限定燃烧室（18）的衬套（12），第一预混合室（14）在燃烧室的上游，以及与第一预混合物流体连通的燃料增压室（40）腔室围绕第一预混合室的至少一部分。向燃烧器供应燃料的方法包括将燃料流过第一预混合室的外表面并进入第一预混合室。

7. 发明授权

US08596069B2 Rational late lean injection 有权
标题翻译：理性迟发注射
公开(公告)号：US08596069B2
公开(公告)日：2013-12-03
申请号：US13349923
申请日：2012-01-13
申请人： Borys Borysovich Shershnyov , Leonid Yul'evich Ginesin , Krishnakumar Venkataraman
发明人： Borys Borysovich Shershnyov , Leonid Yul'evich Ginesin , Krishnakumar Venkataraman
IPC分类号： F02C3/00
CPC分类号： F23R3/005 , F23R3/286 , F23R3/346 , F23R2900/00017
摘要： A combustor section of a gas turbine includes a combustor liner, a sleeve and a fuel-air mixing tube. The combustor liner defines a combustion chamber. The sleeve surrounds the combustor liner. The combustor liner and the sleeve define an annular flow space. The fuel-air mixing tube is configured to channel a mixture of fuel and air and includes an inlet and an outlet. The inlet is in fluid communication with an exterior of the sleeve, and the outlet is in fluid communication with the combustion chamber. The combustor casing encloses the combustor section upstream relative to the inlet of the mixing tube and extends downstream. The sleeve and the combustor casing define a discharge air space. The discharge space is in fluid communication with the mixing tube. The fuel supplying device is located exteriorly of the combustor casing and is configured to inject fuel into the mixing tube.
摘要翻译：燃气轮机的燃烧器部分包括燃烧器衬套，套管和燃料 - 空气混合管。燃烧器衬套限定燃烧室。套筒围绕燃烧器衬套。燃烧器衬套和套管限定环形流动空间。燃料 - 空气混合管构造成引导燃料和空气的混合物并且包括入口和出口。入口与套筒的外部流体连通，并且出口与燃烧室流体连通。燃烧器壳体相对于混合管的入口将燃烧器部分包围在上游并在下游延伸。套筒和燃烧器壳体限定排放空气空间。放电空间与混合管流体连通。燃料供给装置位于燃烧器壳体的外部，并且被配置为将燃料喷射到混合管中。

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