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公开(公告)号:US11146133B2
公开(公告)日:2021-10-12
申请号:US16117158
申请日:2018-08-30
Applicant: General Electric Company
Inventor: Pablo Gabriel Piazza Galarza , Fabian Isaza , Duane Howard Anstead
Abstract: An electric machine may include a rotor shaft that has a hollow region configured to receive a coolant. The hollow region is defined by an inner surface which has a slope that increases from a first inner diameter at a first end to a second inner diameter at a second end. Centrifugal force generated when rotating the rotor shaft causes the coolant to flow across the inner surface of the rotor shaft from the first end to the second end at a velocity depending at least in part on the slope of the inner surface of the rotor shaft. A method of cooling an electric machine includes injecting a coolant into a first end of the hollow region of the rotor shaft, rotating the rotor shaft at an operational rate of rotation, with the rotation generating centrifugal force that causes the coolant to flow from the first end to the second end, transferring heat from the rotor shaft to the coolant.
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公开(公告)号:US20200076257A1
公开(公告)日:2020-03-05
申请号:US16117158
申请日:2018-08-30
Applicant: General Electric Company
Inventor: Pablo Gabriel Piazza Galarza , Fabian Isaza , Duane Howard Anstead
Abstract: An electric machine may include a rotor shaft that has a hollow region configured to receive a coolant. The hollow region is defined by an inner surface which has a slope that increases from a first inner diameter at a first end to a second inner diameter at a second end. Centrifugal force generated when rotating the rotor shaft causes the coolant to flow across the inner surface of the rotor shaft from the first end to the second end at a velocity depending at least in part on the slope of the inner surface of the rotor shaft. A method of cooling an electric machine includes injecting a coolant into a first end of the hollow region of the rotor shaft, rotating the rotor shaft at an operational rate of rotation, with the rotation generating centrifugal force that causes the coolant to flow from the first end to the second end, transferring heat from the rotor shaft to the coolant.
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公开(公告)号:US20140099188A1
公开(公告)日:2014-04-10
申请号:US13713018
申请日:2012-12-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor: Christopher Mark Bordne , Duane Howard Anstead , James John Luz
IPC: F01D25/18
CPC classification number: F01D25/183 , F01D25/18 , F01D25/20
Abstract: Oil sump seal pressurization apparatus for turbine engines are disclosed. An example oil sump seal pressurization apparatus may include a non-rotating oil sump housing a bearing; an oil seal isolating an interior of the oil sump; a passage arranged to supply pressurization air to an outward side of the oil seal; a drain arranged to allow draining of oil and venting of at least some of the pressurization air, the drain being positioned axially between the passage and the oil seal; a wide discourager tooth disposed on the shaft and extending radially outward towards a non-rotating land, which may be disposed axially between the passage and the drain, the wide discourager tooth being spaced apart from the land in a radial direction by a gap, the wide discourager tooth including an upper surface; and/or an adjacent tooth disposed on the shaft and extending radially outward from the shaft.
Abstract translation: 公开了一种用于涡轮发动机的油底壳密封件加压装置。 示例性油底壳密封件加压装置可以包括容纳轴承的非旋转油底壳; 隔离油底壳内部的油封; 通道,其设置成向所述油封的外侧供给加压空气; 排水口,其布置成允许排出油并且排出至少一些加压空气,排水口轴向位于通道和油封之间; 设置在轴上并且径向向外朝向非旋转平台延伸的宽disc ager齿,其可以轴向地设置在通道和排水口之间,宽disc ager齿与径向方向上的间隙与间隙间隔开, 包括上表面的宽disc牙; 和/或相邻的齿设置在轴上并从轴径向向外延伸。
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公开(公告)号:US20170159564A1
公开(公告)日:2017-06-08
申请号:US14962313
申请日:2015-12-08
Applicant: General Electric Company
Inventor: Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
CPC classification number: F02C7/14 , B64D37/34 , F01D25/18 , F02C7/06 , F02C7/224 , F05D2240/40 , F05D2260/213 , Y02T50/675
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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公开(公告)号:US20130283757A1
公开(公告)日:2013-10-31
申请号:US13713013
申请日:2012-12-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor: Christopher Mark Bordne , Duane Howard Anstead , James John Luz
IPC: F02C7/06
CPC classification number: F02C7/06 , F01D25/125 , F01D25/183 , Y02T50/675
Abstract: Oil sump seal pressurization apparatus for a turbine engine are disclosed. An example oil sump seal pressurization apparatus may include an oil sump comprising at least one bearing mounted therein; an oil seal operatively disposed between a non-rotating structural member of the sump and the shaft; a generally radially inwardly oriented passage arranged to supply pressurization air to the outward side of the oil seal; a generally radially outwardly oriented pathway arranged to receive at least some of the pressurization air from the passage, the pathway being at least partially defined by a generally radially outwardly extending arm disposed on the shaft, the arm rotating with the shaft; and/or a windage shield at least partially separating the passage and the pathway, the windage shield being operatively mounted to the non-rotating structural member of the sump.
Abstract translation: 公开了一种用于涡轮发动机的油底壳密封件加压装置。 示例性的油底壳密封件加压装置可以包括其中安装有至少一个轴承的油底壳; 操作地设置在所述贮槽的非旋转结构构件和所述轴之间的油封; 通常径向向内定向的通道,其布置成将加压空气供给到油封的外侧; 通常径向向外定向的路径被布置成从通道接收至少一些加压空气,该通道至少部分地由设置在轴上的大致径向向外延伸的臂限定,所述臂与轴一起旋转; 和/或防风罩至少部分地分开通道和通道,风挡板可操作地安装到贮槽的非旋转结构构件。
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公开(公告)号:US11098647B2
公开(公告)日:2021-08-24
申请号:US16256629
申请日:2019-01-24
Applicant: General Electric Company
Inventor: Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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公开(公告)号:US09567908B2
公开(公告)日:2017-02-14
申请号:US13713013
申请日:2012-12-13
Applicant: General Electric Company
Inventor: Christopher Mark Bordne , Duane Howard Anstead , James John Luz
IPC: F16J15/447 , F02C7/06 , F01D25/12 , F01D25/18
CPC classification number: F02C7/06 , F01D25/125 , F01D25/183 , Y02T50/675
Abstract: Oil sump seal pressurization apparatus for a turbine engine are disclosed. An example oil sump seal pressurization apparatus may include an oil sump comprising at least one bearing mounted therein; an oil seal operatively disposed between a non-rotating structural member of the sump and the shaft; a generally radially inwardly oriented passage arranged to supply pressurization air to the outward side of the oil seal; a generally radially outwardly oriented pathway arranged to receive at least some of the pressurization air from the passage, the pathway being at least partially defined by a generally radially outwardly extending arm disposed on the shaft, the arm rotating with the shaft; and/or a windage shield at least partially separating the passage and the pathway, the windage shield being operatively mounted to the non-rotating structural member of the sump.
Abstract translation: 公开了一种用于涡轮发动机的油底壳密封件加压装置。 示例性的油底壳密封件加压装置可以包括其中安装有至少一个轴承的油底壳; 操作地设置在所述贮槽的非旋转结构构件和所述轴之间的油封; 通常径向向内定向的通道,其布置成将加压空气供给到油封的外侧; 通常径向向外定向的路径被布置成从通道接收至少一些加压空气,该通道至少部分地由设置在轴上的大致径向向外延伸的臂限定,所述臂与轴一起旋转; 和/或防风罩至少部分地分开通道和通道,风挡板可操作地安装到贮槽的非旋转结构构件。
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公开(公告)号:US10648365B2
公开(公告)日:2020-05-12
申请号:US14962217
申请日:2015-12-08
Applicant: General Electric Company
Inventor: Kyle Robert Snow , Brandon Wayne Miller , Duane Howard Anstead , Jonothan Allen Scheetz , Mohammed El Hacin Sennoun , Ning Fang
Abstract: A gas turbine engine having a core engine. The core engine includes an inlet, a compressor section, a combustion section, a turbine section, and an exhaust. The gas turbine engine also includes a bearing sump arranged in the core engine for containing lubrication, the bearing sump and lubrication having an operational range between at least about 0° F. and about 550° F.
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公开(公告)号:US09890846B2
公开(公告)日:2018-02-13
申请号:US14940269
申请日:2015-11-13
Applicant: General Electric Company
Inventor: Mark Gregory Wotzak , Duane Howard Anstead , Bojan Lukovic , James John Luz , Thomas Charles McCarthy , Keith Beatty
IPC: F16H57/02 , F16H57/04 , F02C7/32 , F16H57/027 , F16H57/029
CPC classification number: F16H57/027 , F02C7/32 , F05D2260/605 , F05D2260/608 , F16H57/029 , F16H57/0456 , F16H57/0472
Abstract: A gearbox vent apparatus includes: a gearbox; an accessory contained in a case mounted to the gearbox such than an interior space of the case communicates with an interior space of the gearbox, wherein the case includes a sidewall and an endwall, a hollow drive shaft mounted for rotation inside the case; an annular first seal element mounted to the drive shaft; an annular second seal element mounted to the case and contacting the first seal element so as to define a sealing interface; and a vent tube having a forward end coupled to the endwall in fluid communication with the drive shaft.
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公开(公告)号:US20190153954A1
公开(公告)日:2019-05-23
申请号:US16256629
申请日:2019-01-24
Applicant: General Electric Company
Inventor: Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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