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1. 发明授权

US10352177B2 Airfoil having impingement openings 有权
公开(公告)号：US10352177B2
公开(公告)日：2019-07-16
申请号：US15044697
申请日：2016-02-16
申请人： General Electric Company
发明人： Ronald Scott Bunker , Robert David Briggs , Timothy Deryck Stone
IPC分类号： F01D5/14 , F01D5/18
摘要： An airfoil for a turbine engine having a perimeter wall bounding an interior and defining a pressure side and a suction side, a radially extending rib located within the interior and spaced from the leading edge to define a radially extending leading edge chamber, and at least one impingement opening in the rib defining a flow path aligned with the leading edge.

2. 发明授权

US10280785B2 Shroud assembly for a turbine engine 有权
公开(公告)号：US10280785B2
公开(公告)日：2019-05-07
申请号：US14879277
申请日：2015-10-09
申请人： General Electric Company
发明人： Robert David Briggs , Gulcharan Singh Brainch , Curtis Walton Stover
IPC分类号： F01D11/24
摘要： A shroud assembly for a turbine section of a turbine engine includes a shroud plate in thermal communication with a hot combustion gas flow and a baffle overlying the shroud plate to define a region. One or more shaped cooling features are located along the region such that a cooling fluid flow passing through the region encounters the shaped cooling features to increase the turbulence of the cooling fluid flow.

3. 发明申请

US20170191417A1 ENGINE COMPONENT ASSEMBLY 审中-公开
公开(公告)号：US20170191417A1
公开(公告)日：2017-07-06
申请号：US14989290
申请日：2016-01-06
申请人： General Electric Company
发明人： Ronald Scott Bunker , Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Byron Andrew Pritchard, JR. , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter , Michael Alan Meade
IPC分类号： F02C7/12 , F23R3/00 , F01D5/14 , F01D25/24 , F01D25/08 , F01D9/04
CPC分类号： F01D5/187 , F01D9/065 , F01D25/12 , F05D2240/11 , F05D2250/21 , F05D2250/22 , F05D2250/23 , F05D2250/232 , F05D2250/241 , F05D2250/27 , F05D2260/201 , F05D2260/2214 , F23R3/005 , F23R2900/03044 , F23R2900/03045 , Y02T50/672 , Y02T50/676
摘要： An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, and a second engine component having a first surface in fluid communication with a cooling fluid flow and a second surface spaced from the cooling surface to define a space. A cooling aperture extends through the second engine component. A cooling feature extends from the cooling surface of the first engine component, and is oriented relative to the cooling aperture such that the cooling fluid flow is orthogonal and non-orthogonal to different portions of the cooling feature.

4. 发明申请

US20170107826A1 TURBINE BLADE 审中-公开
公开(公告)号：US20170107826A1
公开(公告)日：2017-04-20
申请号：US14884075
申请日：2015-10-15
申请人： General Electric Company
发明人： Matthew Lee Krumanaker , Weston Nolan Dooley , Steven Robert Brassfield , David Benjamin Helmer , Jeremy Clyde Bailey , Robert David Briggs
IPC分类号： F01D5/18 , F01D25/12 , F01D9/04
CPC分类号： F01D5/187 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2260/202 , F05D2260/204 , Y02T50/676
摘要： An airfoil comprises one or more internal cooling circuits. The cooling circuit can further comprise a near wall cooling mesh, fluidly coupling a supply passage to a mesh plenum. The mesh plenum can be disposed adjacent to the external surface of the airfoil having a plurality of film holes extending between the mesh plenum and the external surface of the airfoil. The mesh plenum can further comprise a cross-sectional area sized to facilitate machining of the film holes without damage to the interior of the airfoil.

5. 发明授权

US09528880B2 Method and system for gas temperature measurement 有权
标题翻译：气体温度测量方法和系统
公开(公告)号：US09528880B2
公开(公告)日：2016-12-27
申请号：US13969186
申请日：2013-08-16
申请人： General Electric Company
发明人： Guanghua Wang , Nirm Velumylum Nirmalan , Ronald Scott Bunker , Todd Garrett Wetzel , Robert Michael Zacharias , Shawn David Wehe , Robert David Briggs
IPC分类号： G01J5/00 , G01K1/14 , G01K13/00 , G01K3/00 , G01J5/10 , G01M15/14 , G01J5/08 , G01J5/60
CPC分类号： G01J5/10 , G01J5/0014 , G01J5/0887 , G01J5/60 , G01M15/14
摘要： A temperature measurement system includes a plurality of filaments. The plurality of filaments are configured to emit thermal radiation in a relatively broad and substantially continuous wavelength band at least partially representative of a temperature of the plurality of filaments. A first and second portion of the filaments has a differing first and a second diameter and/or emissivity, respectively. The system also includes a detector array configured to generate electrical signals at least partially representative of the thermal radiation received from the filaments. The system further includes a controller communicatively coupled to the detector array configured to transform the first electrical signals to a first temperature indication at least partially as a function of the first diameter and/or first emissivity and transform the second electrical signals to a second temperature indication at least partially as a function of the second diameter and/or emissivity.
摘要翻译：温度测量系统包括多个细丝。多根细丝构造成发射至少部分代表多个细丝的温度的相对宽且基本上连续的波长带中的热辐射。长丝的第一和第二部分分别具有不同的第一和第二直径和/或发射率。该系统还包括检测器阵列，该检测器阵列被配置为产生至少部分代表从灯丝接收的热辐射的电信号。所述系统还包括通信地耦合到所述检测器阵列的控制器，所述检测器阵列被配置为至少部分地将所述第一电信号转换为第一温度指示作为所述第一直径和/或第一发射率的函数，并将所述第二电信号转换为第二温度指示至少部分地作为第二直径和/或发射率的函数。

6. 发明申请

US20220170383A1 ENGINE COMPONENT ASSEMBLY 有权
公开(公告)号：US20220170383A1
公开(公告)日：2022-06-02
申请号：US17673426
申请日：2022-02-16
申请人： GENERAL ELECTRIC COMPANY
发明人： Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter
IPC分类号： F01D25/12 , F23R3/00 , F01D5/18 , F23R3/06 , F01D9/04 , F01D11/08 , F02C3/04 , F02C7/18 , F23R3/04
摘要： An engine component assembly with a first substrate having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface, a second substrate having a first surface in fluid communication with a cooling fluid supply and a second surface, different from the first surface, facing and spaced from the cooling surface to define at least one interior cavity. At least one cavity is provided within the first substrate defining a cavity surface where at least a portion of the cavity surface is directly opposite the second surface. At least one cooling aperture extending through the second substrate from the first surface to the second surface, and defining a streamline along which a cooling fluid passes from the cooling fluid supply to the at least one interior cavity.

7. 发明申请

US20200277862A1 AIRFOIL FOR A TURBINE ENGINE 审中-公开
公开(公告)号：US20200277862A1
公开(公告)日：2020-09-03
申请号：US16869831
申请日：2020-05-08
申请人： General Electric Company
发明人： Douglas Gerard Konitzer , Scott Ronald Bunker , Robert David Briggs
IPC分类号： F01D5/18 , F01D25/00 , F01D5/14
摘要： A method and apparatus for minimizing engine weight for a turbine engine by utilizing one or more discrete protuberances disposed on an engine component wall. The wall can have a nominal thickness to decrease engine weight while the protuberances can provide increased discrete thicknesses for providing one or more cooling holes. The increased thickness at the protuberances provides for an increased thickness to provide sufficient length to increase cooling hole effectiveness.

8. 发明授权

US10563514B2 Fastback turbulator 有权
公开(公告)号：US10563514B2
公开(公告)日：2020-02-18
申请号：US15314618
申请日：2015-05-29
申请人： General Electric Company
发明人： Ronald Scott Bunker , Robert David Briggs , Shawn Michael Pearson
IPC分类号： F01D5/14 , F01D9/04 , F23R3/00 , F01D25/12 , F01D5/18
摘要： A structure for disrupting the flow of a fluid is provided, the structure comprising: a first lateral wall and a second lateral wall spaced apart from one another a distance across an X-axis; and a turbulator extending between the first lateral wall and the second lateral wall, the turbulator extending away from the floor. The turbulator includes a first front surface extending between the first lateral wall and the second lateral wall, a second front surface extending between the first lateral wall and the second lateral wall, a first rear surface extending between the first lateral wall and the second lateral wall, the first rear surface extending between the first front surface and the floor, and a second rear surface adjoining the first rear surface and extending between the first lateral wall and the second lateral wall, the second rear surface extending between the second front surface and the floor.

9. 发明授权

US10132166B2 Engine component 有权
公开(公告)号：US10132166B2
公开(公告)日：2018-11-20
申请号：US14633167
申请日：2015-02-27
申请人： General Electric Company
发明人： Ronald Scott Bunker , Robert David Briggs
IPC分类号： F01D5/18 , F01D5/14 , F23R3/00 , F01D9/06 , F01D9/02 , F23R3/50
摘要： An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided upstream of the outlet.

10. 发明申请

US20170306764A1 AIRFOIL FOR A TURBINE ENGINE 审中-公开
公开(公告)号：US20170306764A1
公开(公告)日：2017-10-26
申请号：US15138624
申请日：2016-04-26
申请人： General Electric Company
发明人： Douglas Gerard Konitzer , Scott Ronald Bunker , Robert David Briggs
IPC分类号： F01D5/18 , F01D25/00
CPC分类号： F01D5/186 , F01D5/147 , F01D5/187 , F01D25/002 , F05D2220/323 , F05D2230/20 , F05D2240/30 , F05D2250/185 , F05D2250/232 , F05D2260/202 , F05D2260/22141 , Y02T50/671 , Y02T50/676
摘要： A method and apparatus for minimizing engine weight for a turbine engine by utilizing one or more discrete protuberances disposed on an engine component wall. The wall can have a nominal thickness to decrease engine weight while the protuberances can provide increased discrete thicknesses for providing one or more cooling holes. The increased thickness at the protuberances provides for an increased thickness to provide sufficient length to increase cooling hole effectiveness.

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