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1. 发明公开

US20240159151A1 AIRFOIL FOR A TURBINE ENGINE 审中-公开
公开(公告)号：US20240159151A1
公开(公告)日：2024-05-16
申请号：US18337841
申请日：2023-06-20
申请人： GENERAL ELECTRIC COMPANY
发明人： Douglas Gerard Konitzer , Ronald Scott Bunker , Robert David Briggs
IPC分类号： F01D5/18 , F01D5/14 , 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 , Y02T50/60
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.

2. 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.

3. 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.

4. 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.

5. 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.

6. 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。

7. 发明授权

US11313235B2 Engine component with film hole 有权
公开(公告)号：US11313235B2
公开(公告)日：2022-04-26
申请号：US14659640
申请日：2015-03-17
申请人： General Electric Company
发明人： Ronald Scott Bunker , Frederick Alan Buck , Robert David Briggs , Gulcharan Singh Brainch , Kevin Robert Feldmann
IPC分类号： F01D5/18 , F01D9/06 , F23R3/00
摘要： An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length.

8. 发明授权

US10443407B2 Accelerator insert for a gas turbine engine airfoil 有权
公开(公告)号：US10443407B2
公开(公告)日：2019-10-15
申请号：US15043900
申请日：2016-02-15
申请人： General Electric Company
发明人： Robert David Briggs , Shawn Michael Pearson , Andrew David Kemp , Gulcharan Singh Brainch
IPC分类号： F01D5/18 , F01D25/12 , F01D9/04
摘要： An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.

9. 发明授权

US10378444B2 Engine component for a gas turbine engine 有权
公开(公告)号：US10378444B2
公开(公告)日：2019-08-13
申请号：US14829678
申请日：2015-08-19
申请人： General Electric Company
发明人： Robert Francis Manning , Ronald Scott Bunker , Robert Frederick Bergholz , Robert David Briggs
IPC分类号： F02C3/00 , F02C7/18 , F01D5/18
摘要： An engine component for a gas turbine engine includes a film-cooled recess comprising a contoured portion defining a step. A hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow are fluidly coupled by a passage through the engine component. The passage further comprises an inlet in the cooling surface and an outlet in the step. The inlet, passage and outlet are oriented such that the cooling fluid flowing through the passage and exiting the outlet diffuses within the contoured portion prevents premature mixing out with the hot fluid flow.

10. 发明申请

US20170234140A1 AIRFOIL FOR A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170234140A1
公开(公告)日：2017-08-17
申请号：US15043513
申请日：2016-02-13
申请人： General Electric Company
发明人： Ronald Scott Bunker , Robert David Briggs , Jason Randolph Allen , Kevin Robert Feldmann
IPC分类号： F01D5/18 , F01D25/12 , F01D9/04
CPC分类号： F01D5/187 , F01D5/188 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2250/185 , F05D2260/2212 , F05D2260/607 , Y02T50/676
摘要： A method and apparatus for an airfoil in a gas turbine engine can include an outer surface bounding an interior. At least one flow channel can be defined among one or more full-length and partial-length ribs to further define a cooling circuit within the airfoil. The cooling circuit can have at least one tip turn at the partial-length rib, having at least on fastback turbulator disposed at least partially within the tip turn.

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