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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
CPC分类号： F23R3/10 , F01D9/023 , F01D9/04 , F01D9/06 , F02C3/06 , F04D29/544 , F05D2220/32 , F05D2240/35 , F05D2250/13
摘要： 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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2.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
摘要： 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.
摘要翻译： 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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3.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
摘要： 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.
摘要翻译： 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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公开(公告)号：US11732892B2
公开(公告)日：2023-08-22
申请号：US15912243
申请日：2018-03-05
CPC分类号： F23R3/10 , F01D9/023 , F01D9/04 , F01D9/06 , F02C3/06 , F04D29/544 , F05D2220/32 , F05D2240/35 , F05D2250/13
摘要： 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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5.发明授权System and method relating to axial positioning turbine casings and blade tip clearance in gas turbine engines 有权与涡轮机壳体轴向定位和燃气涡轮发动机叶片间隙相关的系统和方法公开(公告)号：US09441499B2
公开(公告)日：2016-09-13
申请号：US13955721
申请日：2013-07-31
CPC分类号： F01D11/16 , F01D11/18 , F01D25/246 , F05D2250/232
摘要： A system for passively varying an axial position of an inner casing of a gas turbine pursuant to changing pressure in a flowpath during transient engine operation. The system may include: a connection assembly slidably connecting the inner casing to the outer casing for axial movement of the inner casing between a first position and a second position; means for pressurizing the annulus relative to a flowpath pressure; biasing means for axially preloading the inner casing toward the first position; and an inner casing receiving surface configured to receive a pressure in the annulus for axially loading the inner casing in opposition to the axial preload of the biasing means.
摘要翻译： 一种用于在瞬时发动机运转期间根据流路中的变化的压力被动地改变燃气轮机的内壳的轴向位置的系统。 该系统可以包括：连接组件，其可滑动地将内壳体连接到外壳体，用于内壳体在第一位置和第二位置之间的轴向运动; 用于相对于流路压力加压环空的装置; 用于将内壳轴向预加载到第一位置的偏压装置; 以及内壳体接收表面，其构造成在所述环形空间中承受压力，用于与所述偏压装置的轴向预载荷相对轴向地加载所述内壳体。
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公开(公告)号：US09422824B2
公开(公告)日：2016-08-23
申请号：US13654689
申请日：2012-10-18
CPC分类号： F01D11/24 , F01D11/025 , F01D11/14 , F01D11/16 , F01D11/18 , F01D11/20 , F01D25/14 , F01D25/26 , F02C7/12
摘要： Thermal control is provided for a gas turbine casing by supplying thermal control gas from a compressor to a space between an outer casing and an inner casing, and transferring the thermal control gas from the space through the opening in the inner casing via a plurality of holes defined through a plate attached to an outer surface of the inner casing. The holes are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing during operation of the gas turbine via a thermal control gas flow path from radially outside of the inner casing into the interior of the gas turbine.
摘要翻译： 通过从压缩机供给热控制气体到外壳和内壳之间的空间，为燃气轮机壳体提供热控制，并且通过多个孔将热控制气体从空间传递通过内壳体中的开口 通过附接到内壳的外表面的板限定。 孔以预定的不均匀分布布置，其对应于期望的优先冲击图案以提供不均匀的热传递。 燃气轮机热控制组件包括在燃气轮机运行期间通过从内壳的径向外侧到燃气轮机内部的热控制气体流动路径，从内壳提供优先传热的结构。
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公开(公告)号：US09238971B2
公开(公告)日：2016-01-19
申请号：US13654672
申请日：2012-10-18
IPC分类号： F01D11/24
摘要： A device for directing gas impingement to an inner casing of a gas turbine may include a plate configured for attachment to the outer surface of the inner casing. The plate has a first surface opposing the inner casing when the plate is attached to an area of the inner casing and a second surface opposite the first surface. The plate defines a plurality of holes through the plate from the first surface to the second surface. The holes are arranged with a predetermined non-uniform distribution in the plate corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer from the area during operation of the gas turbine so as to control temperature of the inner casing across the area. Various options and modifications are possible. Related gas turbine assemblies are also disclosed.
摘要翻译： 用于将气体冲击引导到燃气涡轮机的内壳体的装置可以包括被配置为附接到内壳体的外表面的板。 当板被附接到内壳的区域和与第一表面相对的第二表面时，板具有与内壳相对的第一表面。 板从第一表面到第二表面限定穿过板的多个孔。 这些孔以对应于期望的优先冲击图案的板中的预定不均匀分布布置，用于在燃气轮机的操作期间从区域提供不均匀的热传递，以便控制内壳跨过该区域的温度。 可以进行各种选择和修改。 还公开了相关的燃气轮机组件。
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公开(公告)号：US20140334925A1
公开(公告)日：2014-11-13
申请号：US13891441
申请日：2013-05-10
IPC分类号： F01D25/24
CPC分类号： F01D25/246 , F01D11/001
摘要： A system for supporting a turbine nozzle includes an inner barrel having a forward end, an aft end and an outer surface that extends between the forward end and the aft end. A first fitting that extends through the outer surface is defined within the inner barrel. The system further includes a nozzle support ring that defines a second fitting that is complementary to the first fitting defined within the inner barrel.
摘要翻译： 用于支撑涡轮喷嘴的系统包括具有前端，后端和在前端和后端之间延伸的外表面的内筒。 在内筒中限定延伸穿过外表面的第一配件。 该系统还包括喷嘴支撑环，其限定与限定在内筒内的第一配件互补的第二配件。
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9.发明申请公开(公告)号：US20140130342A1
公开(公告)日：2014-05-15
申请号：US13673132
申请日：2012-11-09
CPC分类号： B23P11/00 , F01D21/045 , F01D25/28 , F01D25/285 , F05D2230/64 , F05D2230/68 , F16M13/00 , Y10T16/82 , Y10T29/49318 , Y10T29/49721 , Y10T29/53 , Y10T29/53687
摘要： A counter weight for installing and removing a lower portion of an inner casing of a turbine section generally includes a semi-annular main body having a first radially extending mating surface and a second radially extending mating surface. A radial gear rack extends radially outward from the main body. The radial gear rack includes a primary segment that extends a first angular distance between the first radially extending mating surface and the second radially extending mating surface of the main body. A secondary segment of the radial gear rack extends a second angular distance from the second radially extending mating surface of the main body. The secondary segment defines an at least partially linear inner surface and an outer arcuate surface.
摘要翻译： 用于安装和移除涡轮机部分的内壳的下部的配重通常包括具有第一径向延伸配合表面和第二径向延伸配合表面的半环形主体。 径向齿条从主体径向向外延伸。 径向齿条包括主段，该主段在第一径向延伸的匹配表面和主体的第二径向延伸配合表面之间延伸第一角距离。 径向齿条的次级段从主体的第二径向延伸配合表面延伸第二角距离。 次级段限定至少部分线性的内表面和外弧形表面。
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公开(公告)号：US20230358402A1
公开(公告)日：2023-11-09
申请号：US18344954
申请日：2023-06-30
CPC分类号： F23R3/10 , F02C3/06 , F01D9/06 , F01D9/023 , F01D9/04 , F04D29/544 , F05D2240/35 , F05D2220/32 , F05D2250/13
摘要： 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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