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公开(公告)号：US09845690B1
公开(公告)日：2017-12-19
申请号：US15172944
申请日：2016-06-03
Applicant: General Electric Company
Inventor： Andrew Paul Giametta , James Tyson Balkcum, III , David Richard Johns , Stephen Paul Wassynger
CPC classification number: F01D9/023 , F01D11/006 , F05D2240/55 , F05D2240/57 , F16J15/025
Abstract: This disclosure provides systems and methods for sealing flow path components, such as turbomachine airfoils, with a front-leaded seal. A seal channel is defined between a portion of the suction side surface of a first flow path component and a portion of the pressure side of a second flow path component. A seal is retained within the seal channel formed by the pressure side portion and the suction side portion and the seal channel defines a forward opening through which the seal is inserted during installation.
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2.发明申请TURBOMACHINE SEAL ASSEMBLY AND METHOD OF SEALING A ROTOR REGION OF A TURBOMACHINE 审中-公开涡轮密封组件和密封涡轮机转子区域的方法公开(公告)号：US20140154060A1
公开(公告)日：2014-06-05
申请号：US13705825
申请日：2012-12-05
Applicant: GENERAL ELECTRIC COMPANY
IPC: F01D11/00
CPC classification number: F01D11/003 , Y10T29/4932
Abstract: A turbomachine seal assembly includes a rotor disposed about an axial centerline, the rotor having an outer surface. Also included is a stationary component extending circumferentially about the rotor. Further included is at least one primary annular seal ring operably coupled to the stationary component and extending radially inwardly to close proximity with the outer surface of the rotor. Yet further included is a secondary annular seal ring operably coupled to the stationary component and integrally formed with the at least one primary annular seal ring, the secondary annular seal ring extending radially inwardly to close proximity with the outer surface of the rotor.
Abstract translation: 涡轮机械密封组件包括绕轴向中心线设置的转子，转子具有外表面。 还包括围绕转子周向延伸的固定部件。 还包括至少一个初级环形密封环，其可操作地联接到固定部件并且径向向内延伸以紧邻转子的外表面。 另外包括可操作地联接到静止部件并与至少一个主环形密封环一体形成的第二环形密封环，第二环形密封环径向向内延伸以紧邻转子的外表面。
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公开(公告)号：US09938835B2
公开(公告)日：2018-04-10
申请号：US14068776
申请日：2013-10-31
Applicant: General Electric Company
Inventor： Andrew Paul Giametta , David Richard Johns
CPC classification number: F01D5/18 , F01D5/081 , F01D5/187 , F01D5/3007 , Y02T50/676
Abstract: A system for providing cooling of a turbine rotor wheel includes a rotor wheel including a plurality of dovetail slots spaced circumferentially about a peripheral surface of the rotor wheel. Each of the dovetail slots includes a pair of opposite upper slot tangs and a pair of opposite lower slot tangs. The system also includes at least one turbine blade. The turbine blade includes an airfoil, a platform, and a dovetail. The dovetail includes a pair of opposite upper dovetail tangs and a pair of opposite lower dovetail tangs. The dovetail further includes at least one inlet aperture extending longitudinally therethrough. The pair of upper dovetail tangs include a first cooling hole extending therethrough and coupled in flow communication with the at least one inlet aperture.
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公开(公告)号：US09765699B2
公开(公告)日：2017-09-19
申请号：US14585871
申请日：2014-12-30
Applicant: General Electric Company
Inventor： Kevin Richard Kirtley , David Richard Johns , Andrew Paul Giametta , Richard William Johnson
CPC classification number: F02C7/28 , F01D5/081 , F01D11/001 , F01D11/04 , F02C7/18 , F05D2240/127 , F05D2240/81
Abstract: A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside. The port may be configured to direct a coolant expelled therefrom toward the axial projection.
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公开(公告)号：US20160186664A1
公开(公告)日：2016-06-30
申请号：US14585871
申请日：2014-12-30
Applicant: General Electric Company
Inventor： Kevin Richard Kirtley , David Richard Johns , Andrew Paul Giametta , Richard William Johnson
CPC classification number: F02C7/28 , F01D5/081 , F01D11/001 , F01D11/04 , F02C7/18 , F05D2240/127 , F05D2240/81
Abstract: A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside. The port may be configured to direct a coolant expelled therefrom toward the axial projection.
Abstract translation: 一种具有涡轮机的燃气涡轮发动机，其包括定子叶片和转子叶片，所述转子叶片形成在其间限定的沟槽腔中。 密封件可以包括：从定子叶片朝向转子叶片延伸的定子悬垂线，以便包括悬垂顶面，并且与悬垂顶面相对的是突出的下侧; 转子外侧面从平台边缘径向向内延伸，所述转子外侧面与所述突出面的至少一部分相对于所述沟槽的轴向间隙相对; 从所述转子外侧面朝向所述定子叶片延伸的轴向突出部，以与所述定子突出部轴向重叠; 以及内部冷却通道，其延伸穿过定子悬垂端，穿过该突出部下侧形成的端口。 端口可以被配置为将从其排出的冷却剂引向轴向突出部。
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Patent Agency Ranking
公开(公告)号：US09771820B2
公开(公告)日：2017-09-26
申请号：US14585896
申请日：2014-12-30
Applicant: General Electric Company
Inventor： Richard William Johnson , Kevin Richard Kirtley , David Richard Johns , James William Vehr , Andrew Paul Giametta
CPC classification number: F01D11/006 , F01D5/081 , F01D11/001 , F01D11/04 , F05D2240/81
Abstract: A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.
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公开(公告)号：US20160186665A1
公开(公告)日：2016-06-30
申请号：US14585896
申请日：2014-12-30
Applicant: General Electric Company
Inventor： Richard William Johnson , Kevin Richard Kirtley , David Richard Johns , James William Vehr , Andrew Paul Giametta
CPC classification number: F01D11/006 , F01D5/081 , F01D11/001 , F01D11/04 , F05D2240/81
Abstract: A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.
Abstract translation: 一种燃气涡轮发动机中的涡轮，其包括定子叶片和具有形成在沟槽腔中的密封件的转子叶片。 沟槽可以包括限定在定子叶片和转子叶片的相对的内侧面之间的轴向间隙。 密封件可以包括：从定子叶片朝向转子叶片延伸的定子悬垂线，以便包括外侧边缘和内侧边缘，并且在其间限定悬垂面; 转子外侧面从平台边缘径向向内延伸，所述转子外侧面与所述突出面的至少一部分相对于所述沟槽的轴向间隙相对; 以及从转子外侧面朝向定子叶片延伸的第一轴向突起。 转子叶片的定子悬突和第一轴向凸起可被构造成轴向重叠。
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公开(公告)号：US09115810B2
公开(公告)日：2015-08-25
申请号：US14045083
申请日：2013-10-03
Applicant: General Electric Company
IPC: F16J15/447 , F16J15/44
CPC classification number: F16J15/447 , F16J15/442 , Y10T29/49826
Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes multiple sealing device segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the sealing device segments includes a stator interface element, a shoe plate having an extended portion having one or more labyrinth teeth facing the rotor and a load bearing portion, wherein the shoe plate is configured to generate an aerodynamic force between the shoe plate and the rotor. The sealing device segment further includes a secondary seal configured to be in contact with the stator interface element at a radially outer end and configured to be in contact with an elevated nose section of the extended portion of the shoe plate on a radially inner end; and multiple flexible elements attached to the shoe plate and to the stator interface element.
Abstract translation: 提供了一种用于旋转机器的密封组件。 密封组件包括沿周向设置在固定壳体和转子周围的多个密封装置段。 每个密封装置段包括定子界面元件，具有延伸部分的鞋板，该延伸部分具有面向转子的一个或多个迷宫齿轮和承载部分，其中该鞋板构造成在鞋板和 转子。 密封装置段还包括次级密封件，其构造成在径向外端处与定子接口元件接触并且构造成与径向内端上的鞋板延伸部分的升高的鼻部部分接触; 以及附接到鞋板和定子界面元件的多个柔性元件。
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公开(公告)号：US20150118045A1
公开(公告)日：2015-04-30
申请号：US14068776
申请日：2013-10-31
Applicant: General Electric Company
Inventor： Andrew Paul Giametta , David Richard Johns
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/081 , F01D5/187 , F01D5/3007 , Y02T50/676
Abstract: A system for providing cooling of a turbine rotor wheel includes a rotor wheel including a plurality of dovetail slots spaced circumferentially about a peripheral surface of the rotor wheel. Each of the dovetail slots includes a pair of opposite upper slot tangs and a pair of opposite lower slot tangs. The system also includes at least one turbine blade. The turbine blade includes an airfoil, a platform, and a dovetail. The dovetail includes a pair of opposite upper dovetail tangs and a pair of opposite lower dovetail tangs. The dovetail further includes at least one inlet aperture extending longitudinally therethrough. The pair of upper dovetail tangs include a first cooling hole extending therethrough and coupled in flow communication with the at least one inlet aperture.
Abstract translation: 用于提供涡轮转子轮的冷却的系统包括转子轮，该转子轮包括围绕转子轮的外周表面周向间隔开的多个燕尾槽。 每个燕尾槽包括一对相对的上槽脚和一对相对的下槽脚。 该系统还包括至少一个涡轮叶片。 涡轮机叶片包括翼型件，平台和燕尾榫。 燕尾榫包括一对相对的上部燕尾榫和一对相对的下部燕尾榫。 燕尾还包括至少一个纵向延伸穿过的入口孔。 一对上部燕尾榫包括延伸穿过其中并与至少一个入口孔流动连通的第一冷却孔。
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公开(公告)号：US20160298478A1
公开(公告)日：2016-10-13
申请号：US14680083
申请日：2015-04-07
Applicant: General Electric Company
Inventor： Omprakash Samudrala , David Richard Johns , Andrew Paul Giametta , Anthony Christopher Marin
CPC classification number: F01D11/008 , F01D5/147 , F01D5/22 , F01D5/30 , F01D11/001 , F01D11/006 , F05D2220/32 , F05D2230/60 , F05D2240/30 , F05D2240/55 , F05D2240/80 , F05D2250/231 , F05D2250/241
Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a shank assembly may include a component shank with a platform including a first slash face. The shank assembly may include a seal pin slot extending into the first slash face, the seal pin slot having a slot length and a depth, and a seal pin disposed in the seal pin slot, the seal pin having a rounded end positioned adjacent to an end of the seal pin slot.
Abstract translation: 本申请和所得专利提供改进的燃气轮机部件密封。 在一个示例性实施例中，柄组件可以包括具有包括第一斜面的平台的组件柄。 柄组件可以包括延伸到第一斜面的密封销槽，密封销槽具有槽长度和深度，以及设置在密封销槽中的密封销，密封销具有邻近 密封销槽的端部。
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