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公开(公告)号：US20210246829A1
公开(公告)日：2021-08-12
申请号：US16786250
申请日：2020-02-10
Applicant: General Electric Company
Inventor： Jason Ray Gregg , Christopher William Kester , Christopher Paul Cox , David Martin Johnson , Ibrahim Sezer
Abstract: A turbine shroud for turbine systems may include a forward end including a first hook coupled to the turbine casing, an aft end including a second hook coupled to the turbine casing, and a base portion extending between the forward end and the aft end. The base portion may include an inner surface facing a hot gas flow path for the turbine system. Also, the turbine shroud may include a flange extending from the aft end and positioned radially between the base portion and the second hook, a cooling passage positioned within the base portion, adjacent the inner surface, and at least one aft end exhaust conduit in fluid communication with the cooling passage. The aft end exhaust conduit(s) may extend through the aft end, radially between the base portion and the flange.
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公开(公告)号：US09546567B2
公开(公告)日：2017-01-17
申请号：US13633625
申请日：2012-10-02
Applicant: General Electric Company
Inventor： Ravi Shankar Venkata Kasibhotla , Piotr Edward Kobek , Srinivasarao Pakkala , Radu Ioan Danescu , David Martin Johnson
CPC classification number: F01D25/125 , F01D25/14 , F01D25/30 , F02C7/12 , Y02T50/675
Abstract: A system is provided including a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an outer structure having an outer casing, an outer exhaust wall disposed along the exhaust flow path, and an outer cavity disposed between the outer exhaust wall and the outer casing. The turbine exhaust section further includes an inner structure having an inner exhaust wall disposed along the exhaust flow path, an inner cavity disposed between the inner exhaust wall and an inner casing, and a bearing cavity disposed between the inner casing and a bearing housing. In addition, the turbine exhaust section includes a strut extending between the outer structure and the inner structure. The strut includes a first flow passage configured to flow a fluid from the inner cavity to the outer cavity.
Abstract translation: 提供了一种包括涡轮机排气部分的系统。 涡轮排气部包括排气流路。 涡轮机排气部还包括外部结构，其具有外壳，沿排气流路设置的外排气壁和设置在外排气壁与外壳之间的外腔。 涡轮机排气部还包括具有沿着排气流路设置的内排气壁的内结构，设置在内排气壁和内壳之间的内腔，以及设置在内壳和轴承壳之间的轴承腔。 此外，涡轮机排气部分包括在外部结构和内部结构之间延伸的支柱。 支柱包括构造成将流体从内腔流动到外腔的第一流动通道。
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公开(公告)号：US09506366B2
公开(公告)日：2016-11-29
申请号：US13960285
申请日：2013-08-06
Applicant: General Electric Company
Inventor： Radu Ioan Danescu , David Martin Johnson
CPC classification number: F01D11/02 , F01D11/001 , F05D2250/25 , F05D2250/281
Abstract: A helical seal system includes a first component, and a second component rotatable relative to the first component. The second component extends from a high pressure portion to a low pressure portion through an intermediate portion. A helical seal is provided on the intermediate portion of the second component. The helical seal includes at least one thread component having a pitch that is configured and disposed to draw fluids from the low pressure portion toward the high pressure portion when the second component is rotated.
Abstract translation: 螺旋密封系统包括第一部件和相对于第一部件可旋转的第二部件。 第二部件通过中间部分从高压部分延伸到低压部分。 螺旋形密封件设置在第二部件的中间部分上。 所述螺旋形密封件包括至少一个螺纹部件，所述螺纹部件具有螺距，该螺距构造和设置成当第二部件旋转时将流体从低压部分抽向高压部分。
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4.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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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
Applicant: General Electric Company
Inventor： Matthew Stephen Casavant , David Martin Johnson
CPC classification number: F01D11/16 , F01D11/18 , F01D25/246 , F05D2250/232
Abstract: 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.
Abstract translation: 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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Patent Agency Ranking
公开(公告)号：US09422824B2
公开(公告)日：2016-08-23
申请号：US13654689
申请日：2012-10-18
Applicant: General Electric Company
CPC classification number: F01D11/24 , F01D11/025 , F01D11/14 , F01D11/16 , F01D11/18 , F01D11/20 , F01D25/14 , F01D25/26 , F02C7/12
Abstract: 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.
Abstract translation: 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
Applicant: General Electric Company
IPC: F01D11/24
Abstract: 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.
Abstract translation: 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：US20160369631A1
公开(公告)日：2016-12-22
申请号：US15163791
申请日：2016-05-25
Applicant: General Electric Company
Inventor： Richard William Johnson , Bradley James Miller , David Martin Johnson
CPC classification number: F01D5/087 , F01D5/081 , F01D5/084 , F01D5/187 , F01D25/12 , F05D2220/32 , F05D2260/2212
Abstract: A system includes an inducer assembly configured to receive a fluid flow from compressor fluid source and to turn the fluid flow in a substantially circumferential direction into the exit cavity. The inducer assembly includes multiple flow passages. Each flow passage includes an inlet configured to receive the fluid flow and an outlet configured to discharge the fluid flow into the exit cavity, and each flow passage is defined by a first wall portion and a second wall portion extending between the inlet and the outlet. The first wall portion includes a first surface adjacent the outlet that extends into the exit cavity.
Abstract translation: 一种系统包括：诱导器组件，构造成接收来自压缩机流体源的流体流，并将流体流在大致圆周方向上转动到出口腔中。 诱导器组件包括多个流动通道。 每个流动通道包括构造成接收流体流的入口和构造成将流体流排放到出口空腔中的出口，并且每个流动通道由在入口和出口之间延伸的第一壁部分和第二壁部分限定。 第一壁部分包括邻近出口延伸到出口腔中的第一表面。
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9.发明申请CLEARANCE CONTROL SYSTEM FOR A ROTARY MACHINE AND METHOD OF CONTROLLING A CLEARANCE 有权一种旋转机的清除控制系统及其控制方法公开(公告)号：US20150071767A1
公开(公告)日：2015-03-12
申请号：US14025179
申请日：2013-09-12
Applicant: General Electric Company
Inventor： David Martin Johnson , Radu Ioan Danescu
IPC: F01D11/24
CPC classification number: F01D11/24 , F01D11/18 , F01D11/22 , Y02T50/671
Abstract: A clearance control system for a rotary machine includes an outer casing including an outer casing main portion having a first radial thickness, wherein the outer casing is configured to expand at a first time rate of thermal expansion. Also included is an inner casing disposed between the outer casing and a rotary portion, the inner casing including an inner casing main portion having a second radial thickness that is less than the first radial thickness, wherein the inner casing is configured to expand at a second time rate of thermal expansion that is greater than the first time rate of thermal expansion of the outer casing. Further included is an inner casing leg configured to separate from an outer casing leg during expansion of the inner casing and configured to engage the outer casing leg during contraction of the inner casing.
Abstract translation: 一种用于旋转机器的间隙控制系统包括：外壳，包括具有第一径向厚度的外壳主体部分，其中外壳构造成以第一时间热膨胀率膨胀。 还包括设置在外壳和旋转部分之间的内壳，内壳包括具有小于第一径向厚度的第二径向厚度的内壳主体部分，其中内壳构造成在第二径部 时间热膨胀率大于外壳的第一次热膨胀率。 还包括内壳腿，其构造成在内壳膨胀期间与外壳腿分离，并且构造成在内壳收缩期间与外壳腿接合。
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公开(公告)号：US10215059B2
公开(公告)日：2019-02-26
申请号：US15611832
申请日：2017-06-02
Applicant: General Electric Company
Inventor： Wolfgang Franz Dietrich Mohr , Kurt Rechsteiner , David Martin Johnson , Kenneth Damon Black
Abstract: A system and method for active draft control through a combined cycle power plant (CCPP) can initiate a CCPP shutdown, activate the recirculated exhaust gas (REG) system for the turbomachine; measure a HRSG airflow through the HRSG; communicate the HRSG airflow to a controller configured to condition a control signal; and adjust a recirculated exhaust gas volume in accordance with the control signal.
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