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公开(公告)号：US20160298478A1
公开(公告)日：2016-10-13
申请号：US14680083
申请日：2015-04-07
Applicant: General Electric Company
Inventor： Omprakash Samudrala , David Richard Johns , Andrew Paul Giametta , Anthony Christopher Marin
CPC classification number: F01D11/008 , F01D5/147 , F01D5/22 , F01D5/30 , F01D11/001 , F01D11/006 , F05D2220/32 , F05D2230/60 , F05D2240/30 , F05D2240/55 , F05D2240/80 , F05D2250/231 , F05D2250/241
Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a shank assembly may include a component shank with a platform including a first slash face. The shank assembly may include a seal pin slot extending into the first slash face, the seal pin slot having a slot length and a depth, and a seal pin disposed in the seal pin slot, the seal pin having a rounded end positioned adjacent to an end of the seal pin slot.
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，柄组件可以包括具有包括第一斜面的平台的组件柄。 柄组件可以包括延伸到第一斜面的密封销槽，密封销槽具有槽长度和深度，以及设置在密封销槽中的密封销，密封销具有邻近 密封销槽的端部。
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公开(公告)号：US20150056073A1
公开(公告)日：2015-02-26
申请号：US13972667
申请日：2013-08-21
Applicant: General Electric Company
Inventor： Michael James Fedor , David Richard Johns , Richard William Johnson
IPC: F01D5/08
CPC classification number: F01D5/081 , F01D5/08 , F01D5/082 , F01D5/085 , F01D5/087 , F01D5/088 , Y02T50/673 , Y02T50/676
Abstract: A system for cooling an angelwing coupled to a rotor blade in a gas turbine engine is provided. An angelwing coupled to a shank of a rotor blade includes at least one cooling passage extending from at least one inlet opening coupled in flow communication with a gas turbine engine inner wheelspace to at least one outlet opening coupled in flow communication with a gas turbine engine outer rotor/stator cavity. The at least one outlet opening is located in an upper surface of the angelwing. The at least one cooling passage receives pressurized cooling air channeled from the inner wheelspace, such that the pressurized cooling air is channeled into the at least one inlet opening and discharged from the at least one outlet opening.
Abstract translation: 提供了一种用于冷却联接到燃气涡轮发动机中的转子叶片的叶轮的系统。 联接到转子叶片的柄部的角翼包括至少一个冷却通道，其从与燃气涡轮发动机内轮空间流动连通的至少一个入口开口延伸到至少一个与燃气涡轮发动机外部流动连通的出口 转子/定子腔。 至少一个出口开口位于天使的上表面。 所述至少一个冷却通道接收从所述内轮空间引导的加压冷却空气，使得所述加压冷却空气被引导到所述至少一个入口开口中并从所述至少一个出口开口排出。
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3.发明申请ROTATING SEAL CONFIGURATION AND METHOD OF SEALING A ROTATING MEMBER TO A HOUSING 有权旋转密封配置和将旋转部件密封到外壳的方法公开(公告)号：US20140133971A1
公开(公告)日：2014-05-15
申请号：US13676637
申请日：2012-11-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： David Richard Johns , Eric David Roush
IPC: F01D11/02
CPC classification number: F01D11/02 , F01D11/08 , F01D25/24 , F05D2220/32 , F05D2240/55
Abstract: A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face.
Abstract translation: 密封构造包括壳体和相对于壳体旋转地安装的可旋转构件。 可旋转构件具有限定外周面的至少一个部分，其构造成在导致至少一个部分的径向尺寸增加的操作条件期间接触壳体。 所述至少一个部分具有相对的轴向表面，其中每个相对的轴向表面的尺寸轴向更靠近所述外圆周表面的径向向内的所述相对的轴向表面中的另一个，而不是所述外周边面的最远部分。
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公开(公告)号：US09890653B2
公开(公告)日：2018-02-13
申请号：US14680083
申请日：2015-04-07
Applicant: General Electric Company
Inventor： Omprakash Samudrala , David Richard Johns , Andrew Paul Giametta , Anthony Christopher Marin
CPC classification number: F01D11/008 , F01D5/147 , F01D5/22 , F01D5/30 , F01D11/001 , F01D11/006 , F05D2220/32 , F05D2230/60 , F05D2240/30 , F05D2240/55 , F05D2240/80 , F05D2250/231 , F05D2250/241
Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a shank assembly may include a component shank with a platform including a first slash face. The shank assembly may include a seal pin slot extending into the first slash face, the seal pin slot having a slot length and a depth, and a seal pin disposed in the seal pin slot, the seal pin having a rounded end positioned adjacent to an end of the seal pin slot.
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公开(公告)号：US20170350263A1
公开(公告)日：2017-12-07
申请号：US15172944
申请日：2016-06-03
Applicant: General Electric Company
Inventor： Andrew Paul Giametta , James Tyson Balkcum, III , David Richard Johns , Stephen Paul Wassynger
CPC classification number: F01D9/023 , F01D11/006 , F05D2240/55 , F05D2240/57 , F16J15/025
Abstract: This disclosure provides systems and methods for sealing flow path components, such as turbomachine airfoils, with a front-leaded seal. A seal channel is defined between a portion of the suction side surface of a first flow path component and a portion of the pressure side of a second flow path component. A seal is retained within the seal channel formed by the pressure side portion and the suction side portion and the seal channel defines a forward opening through which the seal is inserted during installation.
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Patent Agency Ranking
公开(公告)号：US09404378B2
公开(公告)日：2016-08-02
申请号：US14881765
申请日：2015-10-13
Applicant: General Electric Company
Inventor： David Richard Johns , Eric David Roush
CPC classification number: F01D11/02 , F01D11/08 , F01D25/24 , F05D2220/32 , F05D2240/55
Abstract: A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face.
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公开(公告)号：US20140338364A1
公开(公告)日：2014-11-20
申请号：US13894622
申请日：2013-05-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： David Richard Johns , Mark Andrew Jones
IPC: F01D5/08
CPC classification number: F01D5/084 , F01D5/081 , F01D5/187 , F01D5/3007 , F05D2240/81 , F05D2260/201
Abstract: A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting portion. The airfoil portion further defines the cooling circuit. The turbine rotor blade further includes a platform portion that is disposed radially between the mounting portion and the airfoil. The platform portion includes a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls. A cooling plenum that at least partially defines the cooling circuit is defined within the platform portion. The cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls.
Abstract translation: 涡轮转子叶片包括部分地限定涡轮转子叶片内的冷却回路的安装部分和从安装部分径向向外延伸的翼型部分。 机翼部分进一步限定冷却回路。 涡轮转子叶片还包括一个平台部分，其放置在安装部分和翼型件之间。 平台部分包括底壁，顶壁，前壁，后壁和一对相对的侧壁。 至少部分地限定冷却回路的冷却气室限定在平台部分内。 冷却室至少部分地限定在前壁，后壁和一对相对的侧壁之间。
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公开(公告)号：US09845690B1
公开(公告)日：2017-12-19
申请号：US15172944
申请日：2016-06-03
Applicant: General Electric Company
Inventor： Andrew Paul Giametta , James Tyson Balkcum, III , David Richard Johns , Stephen Paul Wassynger
CPC classification number: F01D9/023 , F01D11/006 , F05D2240/55 , F05D2240/57 , F16J15/025
Abstract: This disclosure provides systems and methods for sealing flow path components, such as turbomachine airfoils, with a front-leaded seal. A seal channel is defined between a portion of the suction side surface of a first flow path component and a portion of the pressure side of a second flow path component. A seal is retained within the seal channel formed by the pressure side portion and the suction side portion and the seal channel defines a forward opening through which the seal is inserted during installation.
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公开(公告)号：US09810070B2
公开(公告)日：2017-11-07
申请号：US13894622
申请日：2013-05-15
Applicant: General Electric Company
Inventor： David Richard Johns , Mark Andrew Jones
CPC classification number: F01D5/084 , F01D5/081 , F01D5/187 , F01D5/3007 , F05D2240/81 , F05D2260/201
Abstract: A turbine rotor blade includes a mounting portion that partially defines a cooling circuit within the turbine rotor blade and an airfoil portion that extends radially outward from the mounting portion. The airfoil portion further defines the cooling circuit. The turbine rotor blade further includes a platform portion that is disposed radially between the mounting portion and the airfoil. The platform portion includes a bottom wall, a top wall, a forward wall, an aft wall and a pair of opposing side walls. A cooling plenum that at least partially defines the cooling circuit is defined within the platform portion. The cooling plenum is at least partially defined between the forward wall, the aft wall and between the pair of opposing side walls.
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公开(公告)号：US20180372112A1
公开(公告)日：2018-12-27
申请号：US15629036
申请日：2017-06-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Deoras Prabhudharwadkar , David Richard Johns
Abstract: A turbomachine and a heat exchange system for the turbomachine are disclosed. The turbomachine includes a stationary component, a rotatable component, an abradable seal component, and a plurality of heat dissipating elements. The rotatable component includes teeth. The abradable seal component is operatively coupled to a surface of the stationary component and disposed facing the teeth to define a clearance there between the abradable seal component and the rotatable component. The plurality of heat dissipating elements is coupled to the abradable seal component. Each of the plurality of heat dissipating elements extends from the abradable seal component through the surface of the stationary component to a turbomachine cavity.
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