公开(公告)号：US20130266416A1

公开(公告)日：2013-10-10

申请号：US13439277

申请日：2012-04-04

申请人： Russell J. Bergman ,  Shawn J. Gregg ,  Michael Papple ,  Paul M. Lutjen ,  Joseph T. Caprario ,  Mohammed Ennacer ,  Thurman Carlo Dabbs

发明人： Russell J. Bergman ,  Shawn J. Gregg ,  Michael Papple ,  Paul M. Lutjen ,  Joseph T. Caprario ,  Mohammed Ennacer ,  Thurman Carlo Dabbs

IPC分类号： F01D25/12 ,  F01D9/02

CPC分类号： F01D25/246 ,  F01D25/14 ,  F05D2240/81

摘要： A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

摘要翻译： 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一集气室流体连通，并且在定子叶片的翼型内具有第一翼型冷却通道。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。

公开(公告)号：US08961108B2

公开(公告)日：2015-02-24

申请号：US13439277

申请日：2012-04-04

申请人： Russell J. Bergman ,  Shawn J. Gregg ,  Michael Papple ,  Paul M. Lutjen ,  Joseph T. Caprario ,  Mohammed Ennacer ,  Thurman Carlo Dabbs

发明人： Russell J. Bergman ,  Shawn J. Gregg ,  Michael Papple ,  Paul M. Lutjen ,  Joseph T. Caprario ,  Mohammed Ennacer ,  Thurman Carlo Dabbs

IPC分类号： F01D9/06

CPC分类号： F01D25/246 ,  F01D25/14 ,  F05D2240/81

摘要： A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.

摘要翻译： 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一集气室流体连通，并且在定子叶片的翼型内具有第一翼型冷却通道。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。

公开(公告)号：US09103225B2

公开(公告)日：2015-08-11

申请号：US13487360

申请日：2012-06-04

申请人： Paul M. Lutjen ,  Shawn J. Gregg ,  Thurman Carlo Dabbs ,  Ken F. Blaney ,  Russell E. Keene ,  Bruce E. Chick

发明人： Paul M. Lutjen ,  Shawn J. Gregg ,  Thurman Carlo Dabbs ,  Ken F. Blaney ,  Russell E. Keene ,  Bruce E. Chick

IPC分类号： F01D11/08

CPC分类号： F01D11/08 ,  F01D1/02 ,  F01D11/24 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/205 ,  F05D2260/2212 ,  F05D2260/2214

摘要： A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.

摘要翻译： 用于燃气涡轮发动机的叶片外部空气密封件包括壁，前钩和后钩。 该壁在前钩和后钩之间延伸，其适于将叶片外部空气密封件安装到燃气涡轮发动机的壳体上。 壁包括沿壁的至少一部分延伸的芯通道。 芯通道径向和轴向地延伸穿过后钩的一部分，以沿着后钩的后缘与一个或多个孔连通。

公开(公告)号：US20130323033A1

公开(公告)日：2013-12-05

申请号：US13487360

申请日：2012-06-04

申请人： Paul M. Lutjen ,  Shawn J. Gregg ,  Thurman Carlo Dabbs ,  Ken F. Blaney ,  Russell E. Keene ,  Bruce E. Chick

发明人： Paul M. Lutjen ,  Shawn J. Gregg ,  Thurman Carlo Dabbs ,  Ken F. Blaney ,  Russell E. Keene ,  Bruce E. Chick

IPC分类号： F01D11/08

CPC分类号： F01D11/08 ,  F01D1/02 ,  F01D11/24 ,  F01D25/12 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/205 ,  F05D2260/2212 ,  F05D2260/2214

摘要： A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook.

公开(公告)号：US20130323032A1

公开(公告)日：2013-12-05

申请号：US13487347

申请日：2012-06-04

申请人： Paul M. Lutjen ,  Thurman Carlo Dabbs

发明人： Paul M. Lutjen ,  Thurman Carlo Dabbs

IPC分类号： F04D29/08

CPC分类号： F04D29/164 ,  F01D11/08 ,  F04D29/526 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

摘要： A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge.

摘要翻译： 根据本公开的示例性实施例的叶片外部空气密封（BOAS）段可以包括密封体，其具有径向内表面和径向外表面，所述径向内表面和径向外表面在第一配合面和第二配合面之间周向延伸， 前缘面和后缘面。 第一配合面，第二配合面，径向外表面和径向内表面中的至少一个可以包括具有突出部的内壁和从突出部沿径向延伸的沿着突出部的长度不间断延伸的底切通道。

公开(公告)号：US08998572B2

公开(公告)日：2015-04-07

申请号：US13487347

申请日：2012-06-04

申请人： Paul M. Lutjen ,  Thurman Carlo Dabbs

发明人： Paul M. Lutjen ,  Thurman Carlo Dabbs

IPC分类号： F01D11/12 ,  F04D29/16

CPC分类号： F04D29/164 ,  F01D11/08 ,  F04D29/526 ,  F05D2240/11 ,  F05D2260/201 ,  Y02T50/676

摘要： A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge.

摘要翻译： 根据本公开的示例性实施例的叶片外部空气密封（BOAS）段可以包括密封体，其具有径向内表面和径向外表面，所述径向内表面和径向外表面在第一配合面和第二配合面之间周向延伸， 前缘面和后缘面。 第一配合面，第二配合面，径向外表面和径向内表面中的至少一个可以包括具有突出部的内壁和从突出部沿径向延伸的沿着突出部的长度不间断延伸的底切通道。

公开(公告)号：US08716623B2

公开(公告)日：2014-05-06

申请号：US13020845

申请日：2011-02-04

申请人： Paul M. Lutjen ,  Kevin J. Ryan ,  Paul S. Bean ,  Paul C. McClay

发明人： Paul M. Lutjen ,  Kevin J. Ryan ,  Paul S. Bean ,  Paul C. McClay

IPC分类号： B23K26/00 ,  B23K26/20

CPC分类号： B23K31/02 ,  B23K15/0046 ,  B23K26/28 ,  B23K33/004 ,  B23K2101/001 ,  F01D11/24 ,  F01D25/12 ,  F05D2230/237 ,  F05D2230/80 ,  F05D2240/11 ,  Y10T29/49318

摘要： A method of closing off a mold plug opening in a turbine component includes the steps of inserting a weld member into an opening to be closed, and to abut a necked portion within a passage leading from the opening. Heat is applied to the weld member, such that a surface of the weld member in contact with the necked portion liquefies, and such that the weld member adheres to the necked portion, closing off the opening. The weld member and application of heat are selected such that the entirety of the weld member does not liquefy, but remains in the opening, without ever having liquefied. A turbine component formed by the method is also disclosed.

摘要翻译： 关闭涡轮机部件中的模具塞开口的方法包括将焊接部件插入待关闭的开口中的步骤，并且邻接从开口引出的通道内的颈缩部分。 对焊接部件施加热量，使得与颈部接触的焊接部件的表面液化，焊接部件粘附到颈部，封闭开口部。 选择焊接构件和施加热量使得焊接构件的整体不会液化，而是保持在开口中，而不会液化。 还公开了通过该方法形成的涡轮机部件。

公开(公告)号：US20130113168A1

公开(公告)日：2013-05-09

申请号：US13289101

申请日：2011-11-04

申请人： Paul M. Lutjen ,  Michael S. Stevens

发明人： Paul M. Lutjen ,  Michael S. Stevens

IPC分类号： F16J15/02 ,  B23P11/00

CPC分类号： F01D11/005 ,  F05D2240/55 ,  F05D2250/71 ,  F16J15/0887 ,  Y10T29/49826

摘要： A gasket assembly for a gas turbine engine includes a seal portion defining outer surfaces for providing sealing contact and a bias portion defining inner structures that are spaced apart from the seal portion for biasing the outer surfaces into sealing contact. The gasket further includes end portions disposed at ends of the seal portion that including a material thickness greater than a thickness of the bias portion.

摘要翻译： 用于燃气涡轮发动机的垫圈组件包括限定用于提供密封接触的外表面的密封部分和限定与密封部分间隔开的内部结构的偏压部分，用于将外表面偏压成密封接触。 垫圈还包括设置在密封部分的端部处的端部，其包括大于偏置部分的厚度的材料厚度。

公开(公告)号：US08177492B2

公开(公告)日：2012-05-15

申请号：US12074501

申请日：2008-03-04

申请人： James N. Knapp ,  Paul M. Lutjen

发明人： James N. Knapp ,  Paul M. Lutjen

IPC分类号： F01D5/20 ,  F01D11/08 ,  F04D29/08 ,  F04D29/18

CPC分类号： F01D5/18 ,  F01D11/08 ,  F05D2240/81 ,  Y02T50/676

摘要： A cooled gas turbine engine component includes a cooling passage, one or more cooling inlet apertures in flow communication with a coolant supply and a first end of the cooling passage, and a coolant flow obstruction inside the cooling passage between the one or more cooling inlet apertures and a second end of the cooling passage and configured to direct a portion of coolant from the one or more cooling inlet apertures toward the first end of the cooling passage.

摘要翻译： 冷却的燃气涡轮发动机部件包括冷却通道，与冷却剂供应源和冷却通道的第一端流动连通的一个或多个冷却入口孔以及冷却通道内的冷却剂流阻塞，该冷却通道在一个或多个冷却入口孔之间 以及冷却通道的第二端，并且构造成将来自所述一个或多个冷却入口孔的冷却剂的一部分引向冷却通道的第一端。

公开(公告)号：US08128366B2

公开(公告)日：2012-03-06

申请号：US12157117

申请日：2008-06-06

申请人： Christopher W. Strock ,  Paul M. Lutjen

发明人： Christopher W. Strock ,  Paul M. Lutjen

IPC分类号： F01D5/18

CPC分类号： F23R3/002 ,  F01D5/186 ,  F05D2250/11 ,  F05D2250/12 ,  F05D2250/141 ,  F05D2260/2212 ,  F23R3/04 ,  F23R2900/03042

摘要： An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall to a first outlet along the exterior surface of the wall for providing film cooling, and first and second rows of vortex-generating structures. The first film cooling passage defines a first interior surface region and a second interior surface region. The first row of vortex-generating structures is located along the first interior surface region, and the second row of vortex-generating structures is located along the second interior surface region. The first and second rows of vortex-generating structures are configured to inducing a pair of vortices in substantially opposite first and second rotational directions in a cooling fluid passing through the first cooling passage prior to reaching the first outlet.

摘要翻译： 用于燃气涡轮发动机的装置包括限定外表面的壁，沿着壁的外表面延伸穿过壁到第一出口的第一膜冷却通道，用于提供膜冷却，以及第一和第二排涡流发生器， 生成结构。 第一膜冷却通道限定第一内表面区域和第二内表面区域。 涡流产生结构的第一排沿着第一内表面区域定位，第二排涡流产生结构沿着第二内表面区域定位。 涡流产生结构的第一排和第二排构造成在到达第一出口之前在通过第一冷却通道的冷却流体中基本上相反的第一和第二旋转方向引起一对涡流。