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公开(公告)号：US12044408B2
公开(公告)日：2024-07-23
申请号：US18344954
申请日：2023-06-30
Applicant: General Electric Company
Inventor： Carl Gerard Schott , Kenneth Damon Black , Matthew Stephen Casavant
CPC classification number: F23R3/10 , F01D9/023 , F01D9/04 , F01D9/06 , F02C3/06 , F04D29/544 , F05D2220/32 , F05D2240/35 , F05D2250/13
Abstract: A diffuser assembly includes a casing at a compressor aft end; an inner barrel member radially inward of the casing; and an array of radial flow splitters extending between the inner barrel member and the casing. Each radial flow splitter includes a leading edge facing into a flow of air, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and an axis extending through the leading edge and the trailing end wall. A width of each radial flow splitter increases from the leading edge to the trailing end wall. The side walls diverge away from the axis in a downstream direction corresponding to the flow of air. Optionally, the side walls also diverge away from the axis in a radial direction between the inner barrel member and the casing.
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公开(公告)号：US11965423B1
公开(公告)日：2024-04-23
申请号：US18196011
申请日：2023-05-11
Applicant: General Electric Company
IPC: F01D19/02
CPC classification number: F01D19/02 , F05D2260/85
Abstract: A system and process for restarting a turbomachine includes a shutdown cooldown protection process implemented by a plant level control system or direct control system of the turbomachine. The system and process for restarting ensure rotating components are cooled as expected prior to a unit restart. This system and process for restarting will lockout an ability to restart if an improper cooldown of rotating components is detected. If this lockout is enabled, delaying restart for the rotating components to cool naturally is needed, or the operator could decide to force cool the components.
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3.发明授权Systems relating to axial positioning turbine casings and blade tip clearance in gas turbine engines 有权与涡轮机壳体中的轴向定位相关的系统和燃气涡轮发动机中的叶片顶端间隙公开(公告)号：US09435218B2
公开(公告)日：2016-09-06
申请号：US13955647
申请日：2013-07-31
Applicant: General Electric Company
Inventor： Matthew Stephen Casavant , Kenneth Damon Black , Christopher Paul Cox
CPC classification number: F01D11/16 , F01D11/14 , F01D11/18 , F01D11/20 , F01D11/22 , F01D11/24 , F05D2240/14
Abstract: A gas turbine engine that includes: a flowpath defined through one of a compressor and a turbine; an inner casing defining an axially tilted outboard boundary of the flowpath, which, relative to the axial tilt, defines a converging direction in which the flowpath converges and a diverging direction in which the flowpath diverges; a row of rotor blades having outer tips that oppose the outboard boundary across a gap clearance defined therebetween; an outer casing concentrically arranged about the inner casing so to form an annulus therebetween; and a connection assembly that slidably connects the inner casing to the outer casing and includes a biasing means for axially preloading the inner casing in the converging direction.
Abstract translation: 一种燃气涡轮发动机，包括：通过压缩机和涡轮机之一限定的流路; 限定所述流路的轴向倾斜的外侧边界的内壳，其相对于所述轴向倾斜限定所述流路会聚的会聚方向和所述流路发散的发散方向; 一排转子叶片，其具有跨越限定在其间的间隙的外侧边缘的外侧尖端; 围绕内壳同心地设置的外壳，以便在它们之间形成环形空间; 以及连接组件，其将内壳滑动地连接到外壳，并且包括用于沿着会聚方向轴向预加载内壳的偏置装置。
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公开(公告)号：US20150330252A1
公开(公告)日：2015-11-19
申请号：US14712723
申请日：2015-05-14
Inventor： Maruthi Prasad Manchikanti , Kenneth Damon Black , Donald Earl Floyd, II , Gregory Allan Crum
Abstract: Embodiments of the present disclosure include a bearing housing of a turbine, wherein the bearing housing is configured to support a shaft of the turbine, and the bearing housing comprises at least one bearing housing ear configured to transfer a load of the bearing housing to an inlet housing of the turbine through a horizontal center line of the bearing housing.
Abstract translation: 本公开的实施例包括涡轮机的轴承壳体，其中轴承壳体构造成支撑涡轮机的轴，并且轴承壳体包括至少一个轴承壳体耳部，其构造成将轴承壳体的负载传递到入口 涡轮机壳体通过轴承座的水平中心线。
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5.发明申请公开(公告)号：US20150047358A1
公开(公告)日：2015-02-19
申请号：US13966667
申请日：2013-08-14
Applicant: General Electric Company
Inventor： Carl Gerard Schott , Kenneth Damon Black , Matthew Stephen Casavant
Abstract: An inner barrel member for a gas turbomachine includes a body having an outer surface, an inner surface and one or more radial flow splitters provided on the outer surface. The one or more radial flow splitters are configured and disposed to be arranged along a combustor centerline at a combustion flow outlet radially inwardly of a transition piece.
Abstract translation: 用于气体涡轮机的内筒构件包括具有外表面的主体，内表面和设置在外表面上的一个或多个径向分流器。 一个或多个径向流分流器构造和设置成沿着燃烧器中心线布置在过渡件径向向内的燃烧流出口处。
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Patent Agency Ranking
6.发明申请公开(公告)号：US20150040581A1
公开(公告)日：2015-02-12
申请号：US13961257
申请日：2013-08-07
Applicant: General Electric Company
Inventor： Kenneth Damon Black
CPC classification number: F01D21/003 , F01D25/00 , F02C7/00 , F05D2250/11 , F05D2250/12 , F05D2250/121 , F05D2250/131 , F05D2250/132 , F05D2250/23 , F05D2250/231 , F05D2260/80 , G02B23/2476
Abstract: A borescope assembly includes a first borescope plug comprising a first perimeter geometry portion. Also included is a second borescope plug comprising a second perimeter geometry portion distinct from the first perimeter geometry portion. Further included is a first borescope hole comprising a first hole geometry portion corresponding to the first perimeter geometry portion of the first borescope plug. Yet further included is a second borescope hole comprising a second hole geometry portion corresponding to the second perimeter geometry portion of the second borescope plug.
Abstract translation: 管状窥镜组件包括第一内窥镜插头，其包括第一周边几何部分。 还包括第二内窥镜插塞，其包括与第一周边几何部分不同的第二周边几何部分。 还包括第一管孔孔，其包括对应于第一管孔塞的第一周边几何部分的第一孔几何部分。 还包括第二孔眼孔，其包括对应于第二内窥镜插头的第二周边几何形状部分的第二孔几何部分。
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公开(公告)号：US20230313708A1
公开(公告)日：2023-10-05
申请号：US17709389
申请日：2022-03-30
Applicant: General Electric Company
Inventor： Kyle Vanceton Mote , Zachary James Taylor , Maruthi Prasad Manchikanti , Kyle Eric Benson , Kenneth Damon Black
CPC classification number: F01D25/28 , F01D25/243 , F05D2230/644 , F05D2260/31 , F05D2260/38
Abstract: A system includes a casing alignment system configured to align an inner wall with an outer wall of a multi-wall casing of a turbomachine having a rotor. The casing alignment system includes a first alignment positioner configured to bias a first lip of the inner wall in a direction of rotation of the rotor disposed within the multi-wall casing. The alignment positioner may include a spring, a fluid-driven alignment positioner, an electric-driven alignment positioner, or a combination thereof. The alignment positioner may be configured to bias the first lip within a first recess adjacent a first flanged coupling between first and second wall sections of the outer wall.
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公开(公告)号：US11732892B2
公开(公告)日：2023-08-22
申请号：US15912243
申请日：2018-03-05
Applicant: General Electric Company
Inventor： Carl Gerard Schott , Kenneth Damon Black , Matthew Stephen Casavant
CPC classification number: F23R3/10 , F01D9/023 , F01D9/04 , F01D9/06 , F02C3/06 , F04D29/544 , F05D2220/32 , F05D2240/35 , F05D2250/13
Abstract: A diffuser assembly includes a casing at a compressor aft end; an inner barrel member radially inward of the casing; and an array of radial flow splitters extending between the inner barrel member and the casing. Each radial flow splitter includes a leading edge facing into a flow of air, a trailing end wall opposite the leading edge, a pair of side walls extending between the leading edge and the trailing end wall, and an axis extending through the leading edge and the trailing end wall. A width of each radial flow splitter increases from the leading edge to the trailing end wall. The side walls diverge away from the axis in a downstream direction corresponding to the flow of air. Optionally, the side walls also diverge away from the axis in a radial direction between the inner barrel member and the casing.
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公开(公告)号：US09546572B2
公开(公告)日：2017-01-17
申请号：US14034635
申请日：2013-09-24
Applicant: General Electric Company
Inventor： Khoa Dang Cao , Kenneth Damon Black
CPC classification number: F01D25/26 , F01D25/243 , F05D2230/64 , F05D2250/51 , Y10T29/4932
Abstract: A turbine system is provided having a first turbine casing and a second turbine casing, the first and second turbine casings together defining an inner wall. The turbine system further includes a first attachment flange extending from a surface of the first turbine casing within the inner wall and a second attachment flange extending from a surface of the second turbine casing within the inner wall. The first attachment flange defines a first aperture and the second attachment flange defines a second aperture. A pin extends through the first aperture and into the second aperture.
Abstract translation: 提供一种具有第一涡轮机壳体和第二涡轮机壳体的涡轮机系统，所述第一和第二涡轮机壳体一起限定内壁。 涡轮机系统还包括从内壁内的第一涡轮机壳体的表面延伸的第一附接凸缘和从内壁内的第二涡轮机壳体的表面延伸的第二附接凸缘。 第一附接凸缘限定第一孔，第二附接凸缘限定第二孔。 销延伸穿过第一孔并进入第二孔。
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10.发明授权Flow sleeve for thermal control of a double-wall turbine shell and related method 有权双壁涡轮壳体热控流量套管及相关方法公开(公告)号：US09453429B2
公开(公告)日：2016-09-27
申请号：US13794136
申请日：2013-03-11
Applicant: General Electric Company
Inventor： Radu Ioan Danescu , David Martin Johnson , Kenneth Damon Black , Christopher Paul Cox , Ozgur Bozkurt
CPC classification number: F01D25/08 , F01D11/24 , F01D19/02 , F01D25/26 , F05D2220/32 , F05D2240/12 , F05D2240/14 , F05D2260/20
Abstract: A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.
Abstract translation: 涡轮壳体包括适于将一个或多个涡轮级包围在燃气涡轮发动机中的至少一个壳体; 至少一个壳体中的空气入口; 固定到所述至少一个壳体的内表面的流动套筒，所述流动套筒包括至少两个弧形段。 每个弧形段包括一个弧形基座，一对侧壁，从基座的径向向外延伸，从而形成由基部，侧壁和内表面限定的周向延伸的流动通道。 空气入口与流动通道对准，并且套筒构造成将在通道中流动的空气沿周向，径向和轴向方向（包括沿着至少一个壳体的内表面）分布在一个或多个涡轮机台附近的空间中。
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