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1. 发明授权

US09822649B2 Integrated combustor and stage 1 nozzle in a gas turbine and method 有权
公开(公告)号：US09822649B2
公开(公告)日：2017-11-21
申请号：US12269411
申请日：2008-11-12
申请人： Lewis Berkley Davis, Jr. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
发明人： Lewis Berkley Davis, Jr. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
IPC分类号： F01C1/00 , F01D9/02 , F01D9/04 , F23R3/00 , F23R3/28 , F23R3/46
CPC分类号： F01D9/023 , F01D9/041 , F23R3/002 , F23R3/286 , F23R3/46 , Y02T50/675
摘要： An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.

2. 发明申请

US20100115953A1 Integrated Combustor and Stage 1 Nozzle in a Gas Turbine and Method 有权
标题翻译：燃气轮机中的一体化燃烧器和1级喷嘴及其方法
公开(公告)号：US20100115953A1
公开(公告)日：2010-05-13
申请号：US12269411
申请日：2008-11-12
申请人： Lewis Berkley Davis, JR. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
发明人： Lewis Berkley Davis, JR. , Willy Steve Ziminsky , Kevin Weston McMahan , Ronald James Chila , Sergey Anatolievich Meshkov
IPC分类号： F23R3/42 , F02C7/22 , F02C3/14
CPC分类号： F01D9/023 , F01D9/041 , F23R3/002 , F23R3/286 , F23R3/46 , Y02T50/675
摘要： An integrated combustor and stage one nozzle in a gas turbine includes a combustion chamber that receives premixed fuel and air from at least one fuel nozzle group at separate axial locations. The combustion chamber includes a liner and a transition piece that deliver hot combustion gas to the turbine. The stage one nozzle, the liner and the transition piece are integrated into a single part. At least one of the axial locations of the one or more fuel nozzle groups includes a plurality of small scale mixing devices that concentrate heat release and reduce flame length.
摘要翻译：在燃气轮机中的一体式燃烧器和一级喷嘴包括燃烧室，其在分开的轴向位置处接收来自至少一个燃料喷嘴组的预混燃料和空气。燃烧室包括将热燃烧气体输送到涡轮机的衬套和过渡件。一级喷嘴，衬管和过渡件集成在一个单一部件中。一个或多个燃料喷嘴组的至少一个轴向位置包括多个小型混合装置，其集中放热并减少火焰长度。

3. 发明授权

US08646276B2 Combustor assembly for a turbine engine with enhanced cooling 有权
标题翻译：用于具有增强冷却的涡轮发动机的燃烧器组件
公开(公告)号：US08646276B2
公开(公告)日：2014-02-11
申请号：US12616304
申请日：2009-11-11
申请人： Lewis Berkley Davis, Jr. , Ronald James Chila
发明人： Lewis Berkley Davis, Jr. , Ronald James Chila
IPC分类号： F02C1/00
CPC分类号： F23R3/005 , F23R3/06 , F23R3/54 , F23R2900/03043 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.
摘要翻译：用于涡轮发动机的燃烧器组件包括燃烧器衬套和围绕燃烧器衬套的流动套管。压缩空气流过位于燃烧器衬套的外表面和流动套管的内表面之间的环形空间。通过流动套筒形成多个冷却孔，以允许压缩空气从流动套筒外部的位置流过冷却孔并进入环形空间。环形空间的高度可以沿着燃烧器组件的长度而变化。因此，流动套管可以具有减小的直径部分，这导致环形空间的高度在某些位置比沿着燃烧器组件的长度的其它位置更小。

4. 发明申请

US20100242487A1 THERMALLY DECOUPLED CAN-ANNULAR TRANSITION PIECE 有权
标题翻译：热释放CAN-ANNULAR过渡片
公开(公告)号：US20100242487A1
公开(公告)日：2010-09-30
申请号：US12413991
申请日：2009-03-30
申请人： Lewis Berkley Davis, JR. , Ronald James Chila
发明人： Lewis Berkley Davis, JR. , Ronald James Chila
IPC分类号： F02C7/12 , F02C7/20 , F23R3/42
CPC分类号： F01D9/023 , F05D2230/642 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/31 , F05D2260/36
摘要： A turbomachine includes a plurality of injection nozzles arranged in a can-annular array and a transition piece including at least one wall that defines a combustion flow passage. A dilution orifice is formed in the at least one wall of the transition piece. The dilution orifice guides dilution gases to the combustion flow passage. A heat shield member is mounted to the at least one wall of the transition piece in the combustion flow passage. The heat shield member includes a body having a first surface and an opposing second surface through which extends a dilution passage. The dilution passage is off-set from the dilution orifice. The heat shield member is spaced from the at least one wall of the transition piece defining a flow region between the at least one wall and the second surface.
摘要翻译：涡轮机包括以罐形环形阵列布置的多个注射喷嘴和包括限定燃烧流动通道的至少一个壁的过渡件。在过渡件的至少一个壁上形成有稀释孔。稀释孔将稀释气体引导到燃烧流动通道。在燃烧流路中的过渡件的至少一个壁上安装有隔热构件。隔热构件包括具有第一表面和相对的第二表面的主体，通过该主体延伸稀释通道。稀释通道从稀释孔偏离。隔热构件与过渡件的至少一个壁间隔开，限定了至少一个壁和第二表面之间的流动区域。

5. 发明申请

US20100242485A1 COMBUSTOR LINER 有权
公开(公告)号：US20100242485A1
公开(公告)日：2010-09-30
申请号：US12414003
申请日：2009-03-30
申请人： Lewis Berkley Davis, JR. , Ronald James Chila
发明人： Lewis Berkley Davis, JR. , Ronald James Chila
IPC分类号： F23R3/42 , F02C7/00
CPC分类号： F23R3/26 , F23M2900/05004 , F23R3/002 , F23R3/02 , F23R3/06 , F23R3/60 , F23R2900/03045 , Y02T50/67 , Y02T50/675
摘要： A combustor within which a combustion zone is defined is provided and includes an annular liner having a first mixing hole defined therein at a first axial position, a flow sleeve, having a second mixing hole defined therein at a second axial position, the flow sleeve surrounding the liner to form a first flow space at an exterior of the liner, a port, coupled to the flow sleeve at the second axial position, which is configured to remove air from the first flow space via the second mixing hole, and a shield, having a third mixing hole defined therein at the second axial position, the shield being disposed to shield the liner and to form a second flow space within the liner, which is communicable with the combustion zone via the third mixing hole and with the first flow space via the first mixing hole.
摘要翻译：设置有燃烧区域的燃烧器被设置并且包括环形衬套，其具有在第一轴向位置处限定在其中的第一混合孔，流动套筒，在第二轴向位置具有限定在其中的第二混合孔，所述衬套在所述衬套的外部形成第一流动空间，在所述第二轴向位置处联接到所述流动套筒的端口，所述端口构造成经由所述第二混合孔从所述第一流动空间移除空气;以及屏蔽件，在第二轴向位置处具有限定在其中的第三混合孔，所述屏蔽件设置成屏蔽衬套并且在衬套内形成第二流动空间，其可经由第三混合孔和第一流动空间与燃烧区域连通通过第一混合孔。

6. 发明授权

US08695322B2 Thermally decoupled can-annular transition piece 有权
标题翻译：热分离的罐环过渡件
公开(公告)号：US08695322B2
公开(公告)日：2014-04-15
申请号：US12413991
申请日：2009-03-30
申请人： Lewis Berkley Davis, Jr. , Ronald James Chila
发明人： Lewis Berkley Davis, Jr. , Ronald James Chila
IPC分类号： F01D9/02 , F23R3/06
CPC分类号： F01D9/023 , F05D2230/642 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/205 , F05D2260/31 , F05D2260/36
摘要： A turbomachine includes a plurality of injection nozzles arranged in a can-annular array and a transition piece including at least one wall that defines a combustion flow passage. A dilution orifice is formed in the at least one wall of the transition piece. The dilution orifice guides dilution gases to the combustion flow passage. A heat shield member is mounted to the at least one wall of the transition piece in the combustion flow passage. The heat shield member includes a body having a first surface and an opposing second surface through which extends a dilution passage. The dilution passage is off-set from the dilution orifice. The heat shield member is spaced from the at least one wall of the transition piece defining a flow region between the at least one wall and the second surface.
摘要翻译：涡轮机包括以罐形环形阵列布置的多个注射喷嘴和包括限定燃烧流动通道的至少一个壁的过渡件。在过渡件的至少一个壁上形成有稀释孔。稀释孔将稀释气体引导到燃烧流动通道。在燃烧流路中的过渡件的至少一个壁上安装有隔热构件。隔热构件包括具有第一表面和相对的第二表面的主体，通过该主体延伸稀释通道。稀释通道从稀释孔偏离。隔热构件与过渡件的至少一个壁间隔开，限定了至少一个壁和第二表面之间的流动区域。

7. 发明授权

US08448416B2 Combustor liner 有权
标题翻译：燃烧器衬管
公开(公告)号：US08448416B2
公开(公告)日：2013-05-28
申请号：US12414003
申请日：2009-03-30
申请人： Lewis Berkley Davis, Jr. , Ronald James Chila
发明人： Lewis Berkley Davis, Jr. , Ronald James Chila
IPC分类号： F23R3/26 , F02C1/00 , F23R3/00
CPC分类号： F23R3/26 , F23M2900/05004 , F23R3/002 , F23R3/02 , F23R3/06 , F23R3/60 , F23R2900/03045 , Y02T50/67 , Y02T50/675
摘要： A combustor within which a combustion zone is defined is provided and includes an annular liner having a first mixing hole defined therein at a first axial position, a flow sleeve, having a second mixing hole defined therein at a second axial position, the flow sleeve surrounding the liner to form a first flow space at an exterior of the liner, a port, coupled to the flow sleeve at the second axial position, which is configured to remove air from the first flow space via the second mixing hole, and a shield, having a third mixing hole defined therein at the second axial position, the shield being disposed to shield the liner and to form a second flow space within the liner, which is communicable with the combustion zone via the third mixing hole and with the first flow space via the first mixing hole.
摘要翻译：设置有燃烧区域的燃烧器被设置并且包括环形衬套，其具有在第一轴向位置处限定在其中的第一混合孔，流动套筒，在第二轴向位置具有限定在其中的第二混合孔，所述衬套在所述衬套的外部形成第一流动空间，在所述第二轴向位置处联接到所述流动套筒的端口，所述端口构造成经由所述第二混合孔从所述第一流动空间移除空气;以及屏蔽件，在第二轴向位置处具有限定在其中的第三混合孔，所述屏蔽件设置成屏蔽衬套并且在衬套内形成第二流动空间，其可经由第三混合孔和第一流动空间与燃烧区域连通通过第一混合孔。

8. 发明申请

US20110107766A1 COMBUSTOR ASSEMBLY FOR A TURBINE ENGINE WITH ENHANCED COOLING 有权
标题翻译：用于具有增强冷却的涡轮发动机的燃烧器组件
公开(公告)号：US20110107766A1
公开(公告)日：2011-05-12
申请号：US12616304
申请日：2009-11-11
申请人： Lewis Berkley DAVIS, JR. , Ronald James Chila
发明人： Lewis Berkley DAVIS, JR. , Ronald James Chila
IPC分类号： F02C7/12
CPC分类号： F23R3/005 , F23R3/06 , F23R3/54 , F23R2900/03043 , F23R2900/03044
摘要： A combustor assembly for a turbine engine includes a combustor liner and a flow sleeve which surrounds the combustor liner. Compressed air flows through an annular space located between an outer surface of the combustor liner and an inner surface of the flow sleeve. A plurality of cooling holes are formed through the flow sleeve to allow compressed air to flow from a position outside the flow sleeve, through the cooling holes, and into the annular space. The height of the annular space may vary along the length of the combustor assembly. Thus, the flow sleeve may have reduced diameter portions which result in the height of the annular space being smaller in certain locations than at other locations along the length of the combustor assembly.
摘要翻译：用于涡轮发动机的燃烧器组件包括燃烧器衬套和围绕燃烧器衬套的流动套管。压缩空气流过位于燃烧器衬套的外表面和流动套管的内表面之间的环形空间。通过流动套筒形成多个冷却孔，以允许压缩空气从流动套筒外部的位置流过冷却孔并进入环形空间。环形空间的高度可以沿着燃烧器组件的长度而变化。因此，流动套管可以具有减小的直径部分，这导致环形空间的高度在某些位置比沿着燃烧器组件的长度的其它位置更小。

9. 发明申请

US20120328421A1 METHODS AND SYSTEMS FOR COOLING A TRANSITION NOZZLE 有权
标题翻译：用于冷却过渡喷嘴的方法和系统
公开(公告)号：US20120328421A1
公开(公告)日：2012-12-27
申请号：US13164887
申请日：2011-06-21
申请人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
发明人： Kevin Weston McMahan , Ronald James Chila , David Richard Johns
IPC分类号： F01D25/24 , B23P15/04
CPC分类号： F01D9/023 , F05D2260/20 , F23R3/002 , F23R3/06 , F23R3/346 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y10T29/4932 , Y10T29/49323
摘要： A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion.
摘要翻译：涡轮组件包括构造成混合燃料和空气的燃料喷嘴和定向成从燃料喷嘴接收燃料和空气混合物的过渡喷嘴。过渡喷嘴包括过渡部分和与过渡部分一体形成的喷嘴部分。过渡喷嘴包括定向成引导空气以便于冷却过渡部分和/或喷嘴部分的多个开口。过渡部分被定向成将燃烧气体引向喷嘴部分。

10. 发明申请

US20100218502A1 EFFUSION COOLED ONE-PIECE CAN COMBUSTOR 有权
标题翻译：有效冷却单罐CAN COMBUSTOR
公开(公告)号：US20100218502A1
公开(公告)日：2010-09-02
申请号：US12395739
申请日：2009-03-02
申请人： Ronald James Chila , Kevin Weston McMahan
发明人： Ronald James Chila , Kevin Weston McMahan
IPC分类号： F23R3/42
CPC分类号： F23R3/06 , F23R3/002 , F23R3/005 , F23R3/46 , F23R2900/03041
摘要： A combustor for an industrial turbine includes a single transition piece transitioning directly from a combustor head-end to a turbine inlet. The transition piece includes an inner surface and an outer surface. The inner surface bounds an interior space for combusted gas flow from the combustor head-end to the turbine inlet. The outer surface at least partially defines an area for compressor discharge air flow. The transition piece includes a plurality of apertures configured to allow compressor discharge air flow into the interior space. Each of the plurality of apertures extends from an entry portion on the outer surface to an exit portion on the inner surface.
摘要翻译：用于工业涡轮机的燃烧器包括直接从燃烧器头端转换到涡轮机入口的单个过渡件。过渡件包括内表面和外表面。内表面限定用于从燃烧器头端到涡轮机入口的燃烧气体流的内部空间。外表面至少部分地限定用于压缩机排出气流的区域。过渡件包括多个孔，其构造成允许压缩机排出空气流入内部空间。多个孔中的每一个从外表面上的入口部分延伸到内表面上的出口部分。

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