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公开(公告)号：US10527151B1
公开(公告)日：2020-01-07
申请号：US16122236
申请日：2018-09-05
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
IPC: F16H57/04
Abstract: A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. There is a gutter with an annular channel. A gear system is connected to the fan shaft. There is a plurality of planetary gears and a ring gear with an aperture that is axially aligned with the annular channel. The ring gear includes a first portion with a first set of opposed angled teeth separated by a trough from a second portion with a second set of opposed angled teeth. A torque frame at least partially supports the gear system. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1 and a low fan pressure ratio of less than 1.45 across the fan blade alone.
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公开(公告)号：US10107231B2
公开(公告)日：2018-10-23
申请号：US14753048
申请日：2015-06-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
Abstract: A geared architecture for a gas turbine engine comprises a fan shaft and a fan supported on the fan shaft and defining a bypass flow ratio greater than about six. A frame supports the fan shaft. A gear system drives the fan shaft. The gear system has a gear reduction ratio of greater than or equal to about 2.3. A torque frame at least partially supports the gear system. An input is coupled to the gear system. A downstream turbine is coupled to rotatably drive the input coupling. The downstream turbine defines a pressure ratio that is greater than about five (5).
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公开(公告)号：US10082105B2
公开(公告)日：2018-09-25
申请号：US15892210
申请日：2018-02-08
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
CPC classification number: F02K3/06 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2240/70 , F05D2260/34 , F05D2260/4031 , F05D2260/40311 , F16H57/0479 , F16H57/0486
Abstract: In one exemplary embodiment, a gas turbine engine includes a bypass flow ratio greater than about ten. A fan supported on a fan shaft having a plurality of fan blades and a low fan pressure ratio of less than 1.45 measured across the fan blades alone. A gutter with an annular channel. A gear system connected to the fan shaft having a gear reduction ratio greater than 2.5, planetary gears, and a ring gear with an aperture that is axially aligned with the annular channel. A torque frame at least partially supports the gear system. A low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1.
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公开(公告)号：US09976437B2
公开(公告)日：2018-05-22
申请号：US14824351
申请日：2015-08-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
CPC classification number: F01D15/12 , F01D1/02 , F01D5/02 , F01D5/027 , F01D25/16 , F01D25/18 , F02C7/32 , F05D2220/32 , F05D2220/36 , F05D2240/70 , F05D2260/34 , F05D2260/40311 , F16H57/0423 , F16H57/0479 , F16H57/0486 , F16H2057/085
Abstract: A turbine engine has a fan shaft. At least one tapered bearing is mounted on the fan shaft. The fan shaft includes at least one passage extending in a direction having at least a radial component, and adjacent the at least one tapered bearing. A fan is mounted for rotation on the tapered bearing. An epicyclic gear train is coupled to drive the fan. The epicyclic gear train includes a carrier supporting intermediate gears that mesh with a sun gear. A ring gear surrounds and meshes with the intermediate gears. Each of the intermediate gears are supported on a respective journal bearing. The epicyclic gear train defines a gear reduction ratio of greater than or equal to about 2.3. A turbine section is coupled to drive the fan through the epicyclic gear train. The turbine section has a fan drive turbine that includes a pressure ratio that is greater than about 5. The fan includes a pressure ratio that is less than about 1.45, and the fan has a bypass ratio of greater than about ten (10).
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公开(公告)号：US20150300197A1
公开(公告)日：2015-10-22
申请号：US14753048
申请日：2015-06-29
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Lawrence E. Portlock , Frederick M. Schwarz
IPC: F01D15/12
CPC classification number: F02K3/06 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2240/70 , F05D2260/34 , F05D2260/4031 , F05D2260/40311 , F16H57/0479 , F16H57/0486
Abstract: A geared architecture for a gas turbine engine comprises a fan shaft and a fan supported on the fan shaft and defining a bypass flow ratio greater than about six. A frame supports the fan shaft. A gear system drives the fan shaft. The gear system has a gear reduction ratio of greater than or equal to about 2.3. A torque frame at least partially supports the gear system. An input is coupled to the gear system. A downstream turbine is coupled to rotatably drive the input coupling. The downstream turbine defines a pressure ratio that is greater than about five (5).
Abstract translation: 用于燃气涡轮发动机的齿轮架构包括风扇轴和支撑在风扇轴上的风扇，并且限定大于约六的旁路流量比。 一个框架支撑风扇轴。 齿轮系驱动风扇轴。 齿轮系统具有大于或等于约2.3的齿轮减速比。 扭矩框架至少部分地支撑齿轮系统。 一个输入端耦合到齿轮系统。 下游涡轮机联接以可旋转地驱动输入联接器。 下游涡轮限定大于约五（5）的压力比。
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Patent Agency Ranking
公开(公告)号：US20150252672A1
公开(公告)日：2015-09-10
申请号：US14287813
申请日：2014-05-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Lawrence E. Portlock
CPC classification number: F16H57/0424 , F01D5/027 , F01D25/18 , F02C7/28 , F02C7/36 , F05D2240/55 , F05D2240/70 , F05D2260/34 , F05D2260/40311 , F05D2260/98 , F16D1/076 , F16H1/28 , F16H57/0402 , F16H57/042 , F16H57/0421 , F16H57/043 , F16H57/0458 , F16H57/0482 , F16H57/0486 , F16H57/08 , Y10T29/49462
Abstract: In one exemplary embodiment, an epicyclic gear train for a turbine engine includes a first shaft that is rotatable about an axis. A ring gear includes first and second portions each having an inner periphery with teeth. The first and second portions are secured to one another at a radial interface. At least one of the first and second portions includes a flange that extends radially outward. The flange is fixed to the first shaft in an axial direction by a fastening element. A carrier supports star gears that mesh with the ring gear. A sun gear meshes with the star gears and is coupled to a second shaft.
Abstract translation: 在一个示例性实施例中，用于涡轮发动机的行星齿轮系包括可围绕轴线旋转的第一轴。 环形齿轮包括第一和第二部分，每个部分具有带齿的内周边。 第一和第二部分在径向界面处彼此固定。 第一和第二部分中的至少一个包括径向向外延伸的凸缘。 凸缘通过紧固元件在轴向方向固定到第一轴。 支架支撑与齿圈啮合的星形齿轮。 太阳齿轮与星形齿轮啮合并且联接到第二轴。
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公开(公告)号：US08931285B2
公开(公告)日：2015-01-13
申请号：US14266888
申请日：2014-05-01
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , William G. Sheridan , Lawrence E. Portlock
IPC: F02C7/06 , F01D25/16 , F01D25/18 , F16H57/04 , F16H57/08 , F16C1/00 , F02C7/10 , F02C7/36 , F02K3/06 , F16N7/34
CPC classification number: F01N3/208 , F01D25/16 , F01D25/18 , F01N3/2066 , F01N11/00 , F01N2610/01 , F01N2610/02 , F01N2610/1406 , F01N2610/142 , F01N2610/148 , F01N2900/1814 , F02C3/10 , F02C7/06 , F02C7/10 , F02C7/36 , F02K3/06 , F05D2260/40311 , F16N7/34 , Y02T10/24 , Y02T50/671 , Y10T29/4932 , Y10T137/0324 , Y10T137/7297
Abstract: In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations.
Abstract translation: 在一个示例性实施例中，燃气涡轮发动机包括风扇，驱动风扇的减速装置和用于沿旋转间隙润滑部件的润滑系统。 润滑系统包括润滑油输入。 固定的第一轴承从润滑剂输入端接收润滑剂并且具有其中润滑剂流动的第一种族。 用于旋转的第二轴承在第一轴承内。 第二轴承具有与所述第一座圈对准的第一开口，使得润滑剂可以从第一座圈通过第一开口流入第一管道。 第一个轴承还有一个润滑剂流入的第二个赛道。 第二轴承具有与第二座圈对准的第二开口，使得润滑剂可以从第二座圈通过第二开口流入第二导管。 第一和第二导管将润滑剂输送到不同的位置。
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公开(公告)号：US20140230452A1
公开(公告)日：2014-08-21
申请号：US14266888
申请日：2014-05-01
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , William G. Sheridan , Lawrence E. Portlock
CPC classification number: F01N3/208 , F01D25/16 , F01D25/18 , F01N3/2066 , F01N11/00 , F01N2610/01 , F01N2610/02 , F01N2610/1406 , F01N2610/142 , F01N2610/148 , F01N2900/1814 , F02C3/10 , F02C7/06 , F02C7/10 , F02C7/36 , F02K3/06 , F05D2260/40311 , F16N7/34 , Y02T10/24 , Y02T50/671 , Y10T29/4932 , Y10T137/0324 , Y10T137/7297
Abstract: In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations.
Abstract translation: 在一个示例性实施例中，燃气涡轮发动机包括风扇，驱动风扇的减速装置和用于沿旋转间隙润滑部件的润滑系统。 润滑系统包括润滑油输入。 固定的第一轴承从润滑剂输入端接收润滑剂并且具有其中润滑剂流动的第一种族。 用于旋转的第二轴承在第一轴承内。 第二轴承具有与所述第一座圈对准的第一开口，使得润滑剂可以从第一座圈通过第一开口流入第一管道。 第一个轴承还有一个润滑剂流入的第二个赛道。 第二轴承具有与第二座圈对准的第二开口，使得润滑剂可以从第二座圈通过第二开口流入第二导管。 第一和第二导管将润滑剂输送到不同的位置。
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公开(公告)号：US20140031162A1
公开(公告)日：2014-01-30
申请号：US13947158
申请日：2013-07-22
Applicant: United Technologies Corporation
Inventor： Loc Quang Duong , Lawrence E. Portlock , Michael E. McCune
IPC: F16H57/04
CPC classification number: F16H57/042 , F16H57/045 , F16H57/0471 , F16H57/0479 , F16H57/0482 , F16H57/082
Abstract: A planetary carrier includes a journal bearing for supporting a planetary gear. The journal bearing receives lubricant to produce a lubricant film to support gear loads. A torque frame is attached to the carrier housing to transmit torque and to prevent twisting of the carrier housing. The torque frame includes several lubricant communication passages to provide lubricant to each of the separate journal bearings. Each of the lubricant communication passages includes an accumulator for storing lubricant during normal operation. The accumulator stores a desired amount of lubricant to provide lubricant to the adjacent journal bearing for the interim period between primary system stoppage and reestablishment of lubricant flow by a secondary system.
Abstract translation: 行星架包括用于支撑行星齿轮的轴颈轴承。 轴颈轴承接收润滑剂以产生润滑剂膜以支撑齿轮负载。 扭矩框架附接到承载壳体以传递扭矩并且防止承载壳体的扭转。 扭矩框架包括若干润滑剂连通通道，以向每个单独的轴颈轴承提供润滑剂。 每个润滑剂连通通道包括用于在正常操作期间储存润滑剂的储液器。 蓄能器存储所需量的润滑剂，以在主系统停止和辅助系统重新建立润滑剂流动之间的临时期间向邻近的轴颈轴承提供润滑剂。
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公开(公告)号：US20210180492A9
公开(公告)日：2021-06-17
申请号：US16006327
申请日：2018-06-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Michael E. McCune , Lawrence E. Portlock
IPC: F01N3/20 , F02C7/10 , F02C7/36 , F01D25/16 , F01D25/18 , F02C7/06 , F01N11/00 , F02K3/06 , F02C3/10 , F16N7/34
Abstract: In an embodiment of the present disclosure, a gas turbine engine includes a fan, a first compressor stage and a second compressor stage, a first turbine stage and a second turbine stage, and wherein said first turbine stage drives said second compressor stage as a high spool, and wherein said second turbine stage drives said first compressor stage as part of a low spool, and a gear train driving said fan with said low spool, and such that said fan and said first compressor stage rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool.
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