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公开(公告)号：US10253690B2
公开(公告)日：2019-04-09
申请号：US15014950
申请日：2016-02-03
发明人： Jonathan Kay Allen , Bradford David Borchert , Jesse Edwin Trout , Ilya Aleksandrovich Slobodyanskiy , Almaz Valeev , Igor Petrovich Sidko , Andrey Pavlovich Subbota
摘要： A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.
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2.发明申请公开(公告)号：US20160222884A1
公开(公告)日：2016-08-04
申请号：US15014981
申请日：2016-02-03
发明人： Jonathan Kay Allen , Bradford David Borchert , Jesse Edwin Trout , Ilya Aleksandrovich Slobodyanskiy , Almaz Valeev , Igor Petrovich Sidko , Matthew Eugene Roberts , Leonid Yulk'evich Ginesin
CPC分类号： F02C3/34 , F01D9/023 , F05D2260/61 , F23C9/08 , F23C2202/50 , F23C2900/09001 , F23R3/005 , F23R3/04 , F23R3/26 , F23R2900/03043 , Y02T50/675
摘要： A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber. The turbine combustor also includes a third volume disposed axially downstream from the first volume and circumferentially about the second volume. The third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from the first volume and from the second volume.
摘要翻译： 一种系统包括涡轮机燃烧器，该涡轮机燃烧器具有构造成接收燃烧流体并将燃烧流体引导到燃烧室中的第一容积。 涡轮机燃烧器包括构造成接收第一排气流并将废气的第一流引导到燃烧室中的第二容积。 涡轮机燃烧器还包括第三容积，其设置在第一容积的轴向下游并且围绕第二容积周向设置。 第三容积构造成接收排气的第二流并且经由抽出口将排气的第二流引导出涡轮机燃烧器，并且第三体积与第一体积和第二体积隔离。
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3.发明申请公开(公告)号：US20160222883A1
公开(公告)日：2016-08-04
申请号：US15014950
申请日：2016-02-03
发明人： Jonathan Kay Allen , Bradford David Borchert , Jesse Edwin Trout , Ilya Aleksandrovich Slobodyanskiy , Almaz Valeev , Igor Petrovich Sidko , Andrey Pavlovich Subbota
CPC分类号： F02C3/34 , F05D2220/32 , F23C9/08 , F23C2202/50 , F23C2900/09001 , F23R3/002 , F23R3/005 , F23R3/04 , F23R3/26 , F23R2900/03043 , Y02T50/675
摘要： A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.
摘要翻译： 一种系统包括涡轮机燃烧器，该涡轮机燃烧器具有构造成接收燃烧流体并将燃烧流体引导到燃烧室中的第一体积，以及构造成接纳排气的第一流动的第二体积。 第二体积构造成将排气的第一流动的第一部分引导到燃烧室中并将排气的第一流动的第二部分引导到与第一容积隔离的第三容积中。 第三容积与提取导管流体连通，该导出管构造成将排气的第一流动的第二部分引导出涡轮机燃烧器。
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4.发明申请SYSTEM AND METHOD FOR AN OXIDANT PASSAGEWAY IN A GAS TURBINE SYSTEM WITH EXHAUST GAS RECIRCULATION 审中-公开在具有排气重燃的气体涡轮机系统中的氧化物渗透系统和方法公开(公告)号：US20160201916A1
公开(公告)日：2016-07-14
申请号：US14992827
申请日：2016-01-11
发明人： Jonathan Kay Allen , Jesse Edwin Trout , Ilya Aleksandrovich Slobodyanskiy , Bradford David Borchert , Michael V. Kazakis , Igor Petrovich Sidko
摘要： A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct an exhaust gas flow toward a head end of the turbine combustor. The radial passageway extends between the flow sleeve and the combustor liner, and the radial passageway is configured to isolate an oxidant flow through the radial passageway from the exhaust gas flow through the passage for a first operating condition and a second operating condition of the turbine combustor. The offset between the combustor liner and the flow sleeve at the first operating condition is greater than the offset between the combustor liner and the flow sleeve at the second operating condition.
摘要翻译： 一种系统包括涡轮机燃烧器。 涡轮机燃烧器具有围绕燃烧室，流动套筒和径向通道设置的燃烧器衬套。 流动套管布置在围绕燃烧器衬套的偏移处以限定通道，其中通道构造成引导废气流朝向涡轮机燃烧器的头端。 径向通道在流动套管和燃烧器衬套之间延伸，并且径向通道构造成将通过径向通道的氧化剂流与通过通道的排气流隔离，用于涡轮机燃烧器的第一操作状态和第二操作状态 。 在第一操作条件下，燃烧器衬套和流动套管之间的偏移量大于在第二操作条件下燃烧器衬套和流动套筒之间的偏移。
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公开(公告)号：US09353952B2
公开(公告)日：2016-05-31
申请号：US13688625
申请日：2012-11-29
发明人： Brandon Taylor Overby , Keith Cletus Belsom , Jonathan Kay Allen , Kyle Eric Benson , Patrick Benedict Melton , Richard Martin DiCintio , Lucas John Stoia , Ronnie Ray Pentecost
IPC分类号： F23R3/48
CPC分类号： F23R3/48
摘要： A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.
摘要翻译： 相邻燃烧器之间的交火管组件包括适于提供来自第一燃烧器和适于连接以提供来自第二燃烧器的流体连通的第一燃烧器和第二套管的流体连通的第一套筒。 第二套筒至少部分地在第一套筒内部延伸。 偏置在第一和第二袖之间。
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6.发明授权公开(公告)号：US10788212B2
公开(公告)日：2020-09-29
申请号：US14992827
申请日：2016-01-11
发明人： Jonathan Kay Allen , Jesse Edwin Trout , Ilya Aleksandrovich Slobodyanskiy , Bradford David Borchert , Michael V. Kazakis , Igor Petrovich Sidko
摘要： A system includes a turbine combustor. The turbine combustor has a combustor liner disposed about a combustion chamber, a flow sleeve, and a radial passageway. The flow sleeve disposed at an offset about the combustor liner to define a passage, wherein the passage is configured to direct an exhaust gas flow toward a head end of the turbine combustor. The radial passageway extends between the flow sleeve and the combustor liner, and the radial passageway is configured to isolate an oxidant flow through the radial passageway from the exhaust gas flow through the passage for a first operating condition and a second operating condition of the turbine combustor. The offset between the combustor liner and the flow sleeve at the first operating condition is greater than the offset between the combustor liner and the flow sleeve at the second operating condition.
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公开(公告)号：US10316746B2
公开(公告)日：2019-06-11
申请号：US15014981
申请日：2016-02-03
发明人： Jonathan Kay Allen , Bradford David Borchert , Jesse Edwin Trout , Ilya Aleksandrovich Slobodyanskiy , Almaz Valeev , Igor Petrovich Sidko , Matthew Eugene Roberts , Leonid Yul'evich Ginesin
IPC分类号： F02C3/34 , F23C9/00 , F23R3/00 , F23R3/06 , F23R3/04 , F23R3/26 , F23C9/08 , F01D9/02 , F23R3/16 , F23R3/28
摘要： A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber. The turbine combustor also includes a third volume disposed axially downstream from the first volume and circumferentially about the second volume. The third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from the first volume and from the second volume.
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公开(公告)号：US20140144122A1
公开(公告)日：2014-05-29
申请号：US13688625
申请日：2012-11-29
发明人： Brandon Taylor Overby , Keith Cletus Belsom , Jonathan Kay Allen , Kyle Eric Benson , Patrick Benedict Melton , Richard Martin DiCintio , Lucas John Stoia , Ronnie Ray Pentecost
IPC分类号： F23R3/48
CPC分类号： F23R3/48
摘要： A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.
摘要翻译： 相邻燃烧器之间的交火管组件包括适于提供来自第一燃烧器和适于连接以提供来自第二燃烧器的流体连通的第一燃烧器和第二套管的流体连通的第一套筒。 第二套筒至少部分地在第一套筒内部延伸。 偏置在第一和第二袖之间。
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