公开(公告)号：US09068469B2

公开(公告)日：2015-06-30

申请号：US13224035

申请日：2011-09-01

申请人： Bradley Reed Tucker ,  Jason Smoke ,  Mark C. Morris

发明人： Bradley Reed Tucker ,  Jason Smoke ,  Mark C. Morris

IPC分类号： F01D11/12 ,  F01D11/00

CPC分类号： F01D11/122 ,  F01D11/006 ,  F05D2230/313 ,  F05D2240/55 ,  F05D2300/123 ,  Y10T29/49297

摘要： A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.

摘要翻译： 燃气涡轮发动机的涡轮部分包括壳体，转子组件和密封组件。 转子组件包括转子盘，联接到转子盘的转子平台以及从转子平台延伸到主流热气流动路径中的转子叶片。 定子组件包括具有定子叶片的定子平台，定子叶片从定子平台延伸到主流热气流动路径中。 所述密封组件包括从所述转子平台沿第一方向延伸的第一流动障碍物，从所述定子平台沿第二方向延伸的第二流动障碍物，所述第一流动障碍物轴向地与所述第二流动盘旋重叠，使得所述第二流动盘旋器为内部 在径向方向上的第一流动捣碎器，施加到第一流动捣碎器的硬涂层，以及施加到第二流动捣碎器的可磨损涂层。

公开(公告)号：US20130058768A1

公开(公告)日：2013-03-07

申请号：US13224035

申请日：2011-09-01

申请人： Bradley Reed Tucker ,  Jason Smoke ,  Mark C. Morris

发明人： Bradley Reed Tucker ,  Jason Smoke ,  Mark C. Morris

IPC分类号： F01D11/00 ,  B21D53/84

CPC分类号： F01D11/122 ,  F01D11/006 ,  F05D2230/313 ,  F05D2240/55 ,  F05D2300/123 ,  Y10T29/49297

摘要： A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.

摘要翻译： 燃气涡轮发动机的涡轮部分包括壳体，转子组件和密封组件。 转子组件包括转子盘，联接到转子盘的转子平台以及从转子平台延伸到主流热气流动路径中的转子叶片。 定子组件包括具有定子叶片的定子平台，定子叶片从定子平台延伸到主流热气流动路径中。 所述密封组件包括从所述转子平台沿第一方向延伸的第一流动障碍物，从所述定子平台沿第二方向延伸的第二流动障碍物，所述第一流动障碍物轴向地与所述第二流动盘旋重叠，使得所述第二流动盘旋器为内部 在径向方向上的第一流动捣碎器，施加到第一流动捣碎器的硬涂层，以及施加到第二流动捣碎器的可磨损涂层。

公开(公告)号：US20100124492A1

公开(公告)日：2010-05-20

申请号：US12272206

申请日：2008-11-17

申请人： Bradley Reed Tucker ,  Mark C. Morris ,  Jason Smoke ,  Daniel Ryan

发明人： Bradley Reed Tucker ,  Mark C. Morris ,  Jason Smoke ,  Daniel Ryan

IPC分类号： F01D9/04 ,  B23P11/00

CPC分类号： F01D5/288 ,  B23K1/0018 ,  B23K1/008 ,  B23K2101/001 ,  B23K2101/34 ,  B23K2103/08 ,  B23K2103/26 ,  F01D9/04 ,  F05D2230/237 ,  F05D2230/60 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2300/121 ,  F05D2300/125 ,  F05D2300/21 ,  F05D2300/2118 ,  Y02T50/67 ,  Y10T29/49323

摘要： Turbine nozzles and methods of manufacturing the turbine nozzles are provided. In an embodiment, by way of example only, a turbine nozzle includes a first ring, a vane, and a first joint. The first ring comprises a single unitary component and having a first opening and including a first metal alloy. The vane includes a first end disposed in the first opening and includes a second metal alloy. The first joint is formed in the first opening between the first ring and the vane and includes a first braze layer and an oxide layer. The first braze layer is disposed adjacent to the oxide layer, and the first braze layer and the oxide layer are disposed between the first ring and the vane.

摘要翻译： 提供涡轮喷嘴和制造涡轮喷嘴的方法。 在一个实施例中，仅作为示例，涡轮喷嘴包括第一环，叶片和第一接头。 第一环包括单个整体部件并且具有第一开口并且包括第一金属合金。 叶片包括设置在第一开口中并包括第二金属合金的第一端。 第一接头形成在第一环和叶片之间的第一开口中，并且包括第一钎焊层和氧化物层。 第一钎焊层邻近氧化物层设置，第一钎焊层和氧化物层设置在第一环和叶片之间。

公开(公告)号：US08047771B2

公开(公告)日：2011-11-01

申请号：US12272206

申请日：2008-11-17

申请人： Bradley Reed Tucker ,  Mark C. Morris ,  Jason Smoke ,  Daniel Ryan

发明人： Bradley Reed Tucker ,  Mark C. Morris ,  Jason Smoke ,  Daniel Ryan

IPC分类号： F04D29/44

CPC分类号： F01D5/288 ,  B23K1/0018 ,  B23K1/008 ,  B23K2101/001 ,  B23K2101/34 ,  B23K2103/08 ,  B23K2103/26 ,  F01D9/04 ,  F05D2230/237 ,  F05D2230/60 ,  F05D2230/90 ,  F05D2240/11 ,  F05D2300/121 ,  F05D2300/125 ,  F05D2300/21 ,  F05D2300/2118 ,  Y02T50/67 ,  Y10T29/49323

摘要： Turbine nozzles and methods of manufacturing the turbine nozzles are provided. In an embodiment, by way of example only, a turbine nozzle includes a first ring, a vane, and a first joint. The first ring comprises a single unitary component and having a first opening and including a first metal alloy. The vane includes a first end disposed in the first opening and includes a second metal alloy. The first joint is formed in the first opening between the first ring and the vane and includes a first braze layer and an oxide layer. The first braze layer is disposed adjacent to the oxide layer, and the first braze layer and the oxide layer are disposed between the first ring and the vane.

摘要翻译： 提供涡轮喷嘴和制造涡轮喷嘴的方法。 在一个实施例中，仅作为示例，涡轮喷嘴包括第一环，叶片和第一接头。 第一环包括单个整体部件并且具有第一开口并且包括第一金属合金。 叶片包括设置在第一开口中并包括第二金属合金的第一端。 第一接头形成在第一环和叶片之间的第一开口中，并且包括第一钎焊层和氧化物层。 第一钎焊层邻近氧化物层设置，第一钎焊层和氧化物层设置在第一环和叶片之间。

公开(公告)号：US08534076B2

公开(公告)日：2013-09-17

申请号：US12481441

申请日：2009-06-09

申请人： Gregory O. Woodcock ,  Bradley Reed Tucker ,  Jason Smoke ,  Stony Kujala ,  Terrel Kuhn

发明人： Gregory O. Woodcock ,  Bradley Reed Tucker ,  Jason Smoke ,  Stony Kujala ,  Terrel Kuhn

IPC分类号： F02C7/20 ,  F04D29/08 ,  F01D11/00

CPC分类号： F01D9/023

摘要： A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.

摘要翻译： 提供燃烧器 - 涡轮机密封接口用于部署在燃气涡轮发动机内。 在一个实施例中，燃烧器 - 涡轮机组件，燃烧器，燃烧器下游的涡轮喷嘴和第一柔性双重密封组件。 第一柔性双密封组件包括密封地联接在燃烧器和涡轮喷嘴之间的顺应性密封壁，密封地设置在柔性密封壁和涡轮喷嘴之间的第一压缩密封件，以及通常由柔性密封壁和 涡轮喷嘴。 第一轴承密封件与第一压缩密封件密封地设置成串联。

公开(公告)号：US20110129342A1

公开(公告)日：2011-06-02

申请号：US12627609

申请日：2009-11-30

申请人： Jason Smoke ,  Bradley Reed Tucker ,  Bob Mitlin ,  Dan Crites ,  Rajiv Rana ,  Alexander MirzaMoghadam

发明人： Jason Smoke ,  Bradley Reed Tucker ,  Bob Mitlin ,  Dan Crites ,  Rajiv Rana ,  Alexander MirzaMoghadam

IPC分类号： F01D5/08

CPC分类号： F01D5/087 ,  F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/676

摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.

摘要翻译： 燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气体流动路径的环形管道壁; 具有延伸到主流气流中的定子叶片的定子组件; 以及在定子组件上游的涡轮转子组件，并且与定子组件限定涡轮机空腔。 涡轮转子组件包括具有前侧和后侧的转子盘，位于转子盘的周边上的转子平台，转子平台限定了后流动盘旋器，安装在转子平台上的转子叶片延伸到主流 气流和安装在转子盘的后侧的后密封板。 尾部密封板具有使得后部密封板保护转子盘免受热气体摄取的半径。

公开(公告)号：US08616832B2

公开(公告)日：2013-12-31

申请号：US12627609

申请日：2009-11-30

申请人： Jason Smoke ,  Bradley Reed Tucker ,  Bob Mitlin ,  Dan Crites ,  Rajiv Rana ,  Alexander MirzaMoghadam

发明人： Jason Smoke ,  Bradley Reed Tucker ,  Bob Mitlin ,  Dan Crites ,  Rajiv Rana ,  Alexander MirzaMoghadam

IPC分类号： F01D5/14

CPC分类号： F01D5/087 ,  F01D5/187 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/676

摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path; a stator assembly with a stator vane extending into the mainstream gas flow; and a turbine rotor assembly upstream of the stator assembly and defining a turbine cavity with the stator assembly. The turbine rotor assembly includes a rotor disk having a forward side and an aft side, a rotor platform positioned on a periphery of the rotor disk, the rotor platform defining an aft flow discourager, a rotor blade mounted on the rotor platform extending into the mainstream gas flow, and an aft seal plate mounted on the aft side of the rotor disk. The aft seal plate has a radius such that the aft seal plate protects the rotor disk from hot gas ingestion.

摘要翻译： 燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气体流动路径的环形管道壁; 具有延伸到主流气流中的定子叶片的定子组件; 以及在定子组件上游的涡轮转子组件，并且与定子组件限定涡轮机空腔。 涡轮转子组件包括具有前侧和后侧的转子盘，位于转子盘的周边上的转子平台，转子平台限定了后流动盘旋器，安装在转子平台上的转子叶片延伸到主流 气流和安装在转子盘的后侧的后密封板。 尾部密封板具有使得后部密封板保护转子盘免受热气体摄取的半径。

公开(公告)号：US20100307166A1

公开(公告)日：2010-12-09

申请号：US12481441

申请日：2009-06-09

申请人： Gregory O. Woodcock ,  Bradley Reed Tucker ,  Jason Smoke ,  Stony Kujala ,  Terrel Kuhn

发明人： Gregory O. Woodcock ,  Bradley Reed Tucker ,  Jason Smoke ,  Stony Kujala ,  Terrel Kuhn

IPC分类号： F02C7/20 ,  F02C3/14

CPC分类号： F01D9/023

摘要： A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.

摘要翻译： 提供燃烧器 - 涡轮机密封接口用于部署在燃气涡轮发动机内。 在一个实施例中，燃烧器 - 涡轮机组件，燃烧器，燃烧器下游的涡轮喷嘴和第一柔性双重密封组件。 第一柔性双密封组件包括密封地联接在燃烧器和涡轮喷嘴之间的顺应性密封壁，密封地设置在柔性密封壁和涡轮喷嘴之间的第一压缩密封件，以及通常由柔性密封壁和 涡轮喷嘴。 第一轴承密封件与第一压缩密封件密封地设置成串联。

公开(公告)号：US08388307B2

公开(公告)日：2013-03-05

申请号：US12506904

申请日：2009-07-21

申请人： Jason Smoke ,  Stony Kujala ,  Gregory O. Woodcock ,  Bradley Reed Tucker

发明人： Jason Smoke ,  Stony Kujala ,  Gregory O. Woodcock ,  Bradley Reed Tucker

IPC分类号： F01D25/24

CPC分类号： F01D9/02 ,  F01D9/042 ,  F05D2260/38 ,  F05D2260/941

摘要： Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE.

摘要翻译： 涡轮喷嘴组件的实施例被提供用于部署在包括第一GTE喷嘴安装界面的燃气涡轮发动机（GTE）内。 在一个实施例中，涡轮喷嘴组件包括涡轮喷嘴流动体，构造成安装到第一GTE喷嘴安装界面的第一安装凸缘以及联接在涡轮喷嘴流体和第一安装凸缘之间的第一径向顺应弹簧构件 。 涡轮喷嘴流动体具有内部喷嘴端壁和外部喷嘴端壁，其固定地联接到内部喷嘴端壁并与其配合以限定通过涡轮喷嘴流体的流动通道。 第一径向顺应弹簧构件适应涡轮喷嘴流体和第一安装凸缘之间的相对热运动，以减轻GTE操作期间的热机械应力。

公开(公告)号：US20110020118A1

公开(公告)日：2011-01-27

申请号：US12506904

申请日：2009-07-21

申请人： Jason Smoke ,  Stony Kujala ,  Gregory O. Woodcock ,  Bradley Reed Tucker

发明人： Jason Smoke ,  Stony Kujala ,  Gregory O. Woodcock ,  Bradley Reed Tucker

IPC分类号： F01D9/04

CPC分类号： F01D9/02 ,  F01D9/042 ,  F05D2260/38 ,  F05D2260/941

摘要： Embodiments of a turbine nozzle assembly are provided for deployment within a gas turbine engine (GTE) including a first GTE-nozzle mounting interface. In one embodiment, the turbine nozzle assembly includes a turbine nozzle flowbody, a first mounting flange configured to be mounted to the first GTE-nozzle mounting interface, and a first radially-compliant spring member coupled between the turbine nozzle flowbody and the first mounting flange. The turbine nozzle flowbody has an inner nozzle endwall and an outer nozzle endwall, which is fixedly coupled to the inner nozzle endwall and which cooperates therewith to define a flow passage through the turbine nozzle flowbody. The first radially-compliant spring member accommodates relative thermal movement between the turbine nozzle flowbody and the first mounting flange to alleviate thermomechanical stress during operation of the GTE.

摘要翻译： 涡轮喷嘴组件的实施例被提供用于部署在包括第一GTE喷嘴安装界面的燃气涡轮发动机（GTE）内。 在一个实施例中，涡轮喷嘴组件包括涡轮喷嘴流动体，构造成安装到第一GTE喷嘴安装界面的第一安装凸缘以及联接在涡轮喷嘴流体和第一安装凸缘之间的第一径向顺应弹簧构件 。 涡轮喷嘴流动体具有内部喷嘴端壁和外部喷嘴端壁，其固定地联接到内部喷嘴端壁并与其配合以限定通过涡轮喷嘴流动体的流动通道。 第一径向顺应弹簧构件适应涡轮喷嘴流体和第一安装凸缘之间的相对热运动，以减轻GTE操作期间的热机械应力。