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公开(公告)号：US09945244B2
公开(公告)日：2018-04-17
申请号：US14825636
申请日：2015-08-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Frederic Woodrow Roberts , Victor John Morgan , Matthew Troy Hafner
CPC classification number: F01D11/22 , F05D2240/11 , F05D2260/50 , F05D2300/6033
Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, and a biasing apparatus. The biasing apparatus is arranged and disposed to bias the inner shroud in a direction away from the hot gas path, loading the inner shroud to the outer shroud. In another embodiment, the biasing apparatus is a springless biasing apparatus including at least one bellows, at least one thrust piston, or a combination of at least one bellows and at least one thrust piston. A method for loading the turbine shroud assembly is disclosed including biasing the inner shroud having a surface adjacent to a hot gas path in a direction away from the hot gas path toward the outer shroud, wherein biasing the inner shroud includes a biasing force exerted by the biasing apparatus.
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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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Patent Agency Ranking
公开(公告)号：US09759081B2
公开(公告)日：2017-09-12
申请号：US14049020
申请日：2013-10-08
Applicant: General Electric Company
Inventor： Victor John Morgan , Gregory Thomas Foster , Neelesh Nandkumar Sarawate , David Wayne Weber
CPC classification number: F01D11/08 , F01D9/041 , F01D11/003 , F05D2230/60 , F05D2260/38 , Y10T29/4932
Abstract: A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.
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公开(公告)号：US09423781B2
公开(公告)日：2016-08-23
申请号：US13853332
申请日：2013-03-29
Applicant: General Electric Company
Inventor： Victor John Morgan , Tomas A. Velez
CPC classification number: G05B17/02
Abstract: A method to control an power generation plant including: applying control settings to operate the plant; collecting plant data indicative of the performance of the plant; applying the control settings to a model of the plant; collecting prediction data from the model; comparing the plant data to the predicted data and adjusting the control settings applied to the plant and model; perturbing the control settings and applying the perturbed control settings to operate the plant and the model; collecting perturbed plant data and perturbed prediction data, and modifying the model if the perturbed plant data represents an improvement as compared to the perturbed prediction data.
Abstract translation: 一种控制发电厂的方法，包括：对工厂进行控制设定; 收集指示工厂性能的工厂数据; 将控制设置应用于工厂的模型; 从模型收集预测数据; 将工厂数据与预测数据进行比较，并调整应用于工厂和模型的控制设置; 扰乱控制设置并应用扰动控制设置来操作设备和模型; 收集扰动的植物数据和扰动的预测数据，以及如果扰动的植物数据表示与扰动的预测数据相比的改进，则修改该模型。
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公开(公告)号：US20160208633A1
公开(公告)日：2016-07-21
申请号：US14597772
申请日：2015-01-15
Applicant: General Electric Company
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D25/246 , F05D2230/60 , F05D2230/90 , F05D2240/11 , F05D2300/6033 , F05D2300/611
Abstract: A turbine shroud assembly includes a plurality of arcuate shroud block assemblies annularly arranged to form a shroud segment. The plurality of shroud block assemblies includes a first shroud block assembly having a shroud block and a second shroud block assembly having a shroud block. The first shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the first shroud block. The second shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the second shroud block.
Abstract translation: 涡轮机罩组件包括多个弓形护罩块组件，其环形地设置成形成护罩段。 多个护罩块组件包括具有护罩块的第一护罩块组件和具有护罩块的第二护罩块组件。 第一护罩块组件包括密封接口构件和护罩密封件。 密封接口构件具有与第一护罩块的径向侧表面相邻的侧部。 第二护罩块组件包括密封接口构件和护罩密封件。 密封接口构件具有与第二护罩块的径向侧表面相邻的侧部。
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公开(公告)号：US20140321994A1
公开(公告)日：2014-10-30
申请号：US13853556
申请日：2013-03-29
Applicant: General Electric Company
Inventor： Brian Gene Brzek , Victor John Morgan , Benjamin Paul Lacy
CPC classification number: F01D25/12 , F01D5/183 , F01D5/186 , F01D9/02 , F01D9/041 , F05D2300/514 , F05D2300/612 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: A hot gas path component for a turbine system is disclosed. The hot gas path component includes a shell and one or more porous media having an exterior surface and an interior surface and positioned adjacent the shell. The one or more porous media is configured to include varying permeability in one of an axial direction, a radial direction, an axial and a radial direction, an axial and a circumferential direction, a radial and a circumferential direction or an axial, a radial and a circumferential direction, the porous media is positioned adjacent the shell. The one or more porous media is further configured to control one of an axial, a radial, an axial and a radial, an axial and a circumferential, a radial and a circumferential or an axial, a radial and a circumferential flow of a cooling medium flowing therethrough.
Abstract translation: 公开了一种用于涡轮机系统的热气体路径部件。 热气体路径部件包括壳体和一个或多个多孔介质，其具有外表面和内表面并且邻近壳体定位。 一个或多个多孔介质被配置为包括在轴向方向，径向方向，轴向和径向方向，轴向和圆周方向，径向和圆周方向或轴向，径向和 圆周方向，多孔介质位于壳体附近。 一个或多个多孔介质还被构造成控制冷却介质的轴向，径向，轴向和径向，轴向和周向的径向和周向或轴向的径向和周向流动 流过
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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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