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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：US20160237912A1
公开(公告)日：2016-08-18
申请号：US14623570
申请日：2015-02-17
Applicant: General Electric Company
Inventor： Kevin Richard Kirtley , Victor John Morgan
IPC: F02C7/28
CPC classification number: F02C7/28 , F01D11/00 , F01D11/001 , F01D11/005 , F05D2240/11 , F05D2240/55 , F16J15/02
Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a gas turbine segment seal assembly may include a first tapered segment seal with a first tapered portion having a first tapered surface and a first taper angle. The gas turbine segment seal assembly may include a second tapered segment seal with a second tapered portion having a second tapered surface and a second taper angle. The gas turbine segment seal assembly may include a seal pin positioned in between the first tapered segment seal and the second segment seal and adjacent to the first tapered surface and the second tapered surface.
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，燃气涡轮机段密封组件可以包括具有第一锥形部分的第一锥形段密封件，该第一锥形部分具有第一锥形表面和第一锥形角度。 燃气轮机段密封组件可以包括具有第二锥形部分的第二锥形段密封件，第二锥形部分具有第二锥形表面和第二锥形角度。 燃气轮机段密封组件可以包括位于第一锥形段密封件和第二段密封件之间并且紧邻第一锥形表面和第二锥形表面的密封销。
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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：US09863323B2
公开(公告)日：2018-01-09
申请号：US14623570
申请日：2015-02-17
Applicant: General Electric Company
Inventor： Kevin Richard Kirtley , Victor John Morgan
CPC classification number: F02C7/28 , F01D11/00 , F01D11/001 , F01D11/005 , F05D2240/11 , F05D2240/55 , F16J15/02
Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a gas turbine segment seal assembly may include a first tapered segment seal with a first tapered portion having a first tapered surface and a first taper angle. The gas turbine segment seal assembly may include a second tapered segment seal with a second tapered portion having a second tapered surface and a second taper angle. The gas turbine segment seal assembly may include a seal pin positioned in between the first tapered segment seal and the second segment seal and adjacent to the first tapered surface and the second tapered surface.
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公开(公告)号：US09334803B2
公开(公告)日：2016-05-10
申请号：US13971196
申请日：2013-08-20
Applicant: General Electric Company
Inventor： John Charles Intile , Kevin Richard Kirtley
CPC classification number: F02C7/12 , F02C7/08 , F05D2260/205 , F05D2260/213 , F05D2260/2322
Abstract: A method of recovering heat energy from a cooling medium used to cool hot gas path components in a turbine engine includes cooling one or more hot gas path components with the cooling medium; supplying spent cooling medium used to cool the one or more hot gas path components to a heat exchanger; supplying air (e.g., compressor discharge air) to the heat exchanger so as to be in heat exchange relationship with the spent cooling medium and thereby add heat to the compressor discharge air; and supplying the air heated in the heat exchanger to at least one combustor.
Abstract translation: 从用于冷却涡轮发动机中的热气路径部件的冷却介质回收热能的方法包括用冷却介质冷却一个或多个热气路径部件; 将用于将一个或多个热气路径部件冷却到用于热交换器的用过的冷却介质; 向热交换器供给空气（例如，压缩机排出空气），以与废冷却介质处于热交换关系，从而向压缩机排放空气加热; 以及将在热交换器中加热的空气供给到至少一个燃烧器。
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Patent Agency Ranking
公开(公告)号：US20140154062A1
公开(公告)日：2014-06-05
申请号：US13690485
申请日：2012-11-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： David Wayne Weber , Kevin Richard Kirtley , Victor John Morgan , Neelesh Nandkumar Sarawate
IPC: F02C7/28
CPC classification number: F02C7/28 , F01D11/00 , F01D11/005 , F01D11/006 , F05D2230/90 , F05D2240/55 , F05D2240/57 , F05D2300/43 , F05D2300/611 , Y10T29/49229
Abstract: A seal for placement in a slot between two turbine components of a gas turbine to seal a gap between the components may include a sealing element sized so as to be capable of placement within the slot and of substantially sealing the gap during operation of the gas turbine. A sacrificial coating may be located on the sealing element. The sacrificial coating may be configured with a size substantially conforming to a size of the slot, the sacrificial coating including a material that is removable from the sealing element via heating to a temperature achieved during operation of the gas turbine. Related gas turbine assemblies and methods of assembly are also disclosed.
Abstract translation: 用于放置在燃气涡轮机的两个涡轮机部件之间以密封部件之间的间隙的狭槽中的密封件可以包括密封元件，其尺寸设计成能够放置在槽内并且在燃气轮机的操作期间基本上密封间隙 。 牺牲涂层可以位于密封元件上。 牺牲涂层可以被配置成基本上符合狭缝尺寸的尺寸，牺牲涂层包括可通过加热将其从密封元件移除到燃气涡轮机运行期间达到的温度的材料。 还公开了相关的燃气轮机组件和组装方法。
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公开(公告)号：US20180010467A1
公开(公告)日：2018-01-11
申请号：US15203027
申请日：2016-07-06
Applicant: General Electric Company
Inventor： Xiuzhang James Zhang , Kevin Richard Kirtley , Lisa DeBellis
CPC classification number: F01D5/225 , F01D5/20 , F01D11/08 , F05D2220/32 , F05D2240/24 , F05D2240/307 , F05D2240/55 , Y02T50/671 , Y02T50/673
Abstract: A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.
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8.发明申请公开(公告)号：US20140116660A1
公开(公告)日：2014-05-01
申请号：US13664458
申请日：2012-10-31
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/187 , F01D5/288 , F05D2260/204 , Y02T50/672 , Y02T50/676 , Y02T50/6765
Abstract: A method of fabricating a component is provided. The component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one interior space. The fabrication method includes forming at least one groove in the outer substrate surface. Each groove extends at least partially along the outer substrate surface and has an asymmetric cross-section. The method further includes forming at least one access hole in the substrate. Each access hole connects the respective groove in fluid communication with the respective interior space. A coating is disposed over at least a portion of the substrate surface, such that the groove(s) and the coating together define one or more channels for cooling the component. A component is also disclose and has at least one groove with an asymmetric cross-section.
Abstract translation: 提供了一种制造组件的方法。 该部件包括具有外表面和内表面的基底，其中内表面限定至少一个内部空间。 制造方法包括在外基板表面中形成至少一个凹槽。 每个槽至少部分地沿着外部衬底表面延伸并且具有不对称的横截面。 该方法还包括在基板中形成至少一个进入孔。 每个进入孔连接相应的凹槽，与相应的内部空间流体连通。 涂层被设置在衬底表面的至少一部分上，使得沟槽和涂层一起限定一个或多个用于冷却部件的通道。 还公开了一种组件，并且具有至少一个具有不对称横截面的凹槽。
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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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