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公开(公告)号：US20140178180A1
公开(公告)日：2014-06-26
申请号：US14190159
申请日：2014-02-26
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
CPC classification number: F02C7/36 , F01D25/18 , F02C3/107 , F02C7/06 , F02K3/06 , F05D2260/4031 , Y02T50/671
Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.
Abstract translation: 用于燃气涡轮发动机的风扇驱动齿轮系统包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统和齿轮系统的柔性支撑部分的安装件。 支持风扇驱动齿轮系统的润滑系统为齿轮系统提供润滑剂，并去除由齿轮系产生的热能。 润滑系统包括用于去除等于齿轮系统中输入的功率小于约2％的热能的能力。
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公开(公告)号：US20140087907A1
公开(公告)日：2014-03-27
申请号：US13727868
申请日：2012-12-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James B. Coffin , Michael E. McCune , William G. Sheridan
IPC: F16H57/04
CPC classification number: F16H57/0467 , F01D25/18 , F02C7/36 , F05D2220/32 , F05D2260/30 , F05D2260/31 , F05D2260/40311 , F05D2260/98 , F16H57/025 , F16H57/0479
Abstract: An example epicyclic gear train assembly includes a flexure pin received by a carrier. The flexure pin and the carrier respectively include first and second pin apertures configured to receive a retainer pin. The flexure pin further includes a lubricant conduit separate from the first pin aperture.
Abstract translation: 示例性行星齿轮系组件包括由载体接收的挠曲销。 挠曲销和托架分别包括构造成接收保持销的第一和第二销孔。 挠曲销还包括与第一销孔分开的润滑剂导管。
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公开(公告)号：US20140020404A1
公开(公告)日：2014-01-23
申请号：US14034720
申请日：2013-09-24
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann , Jason Husband
IPC: F02C7/06
CPC classification number: F02C7/06 , F01D25/18 , F02C3/107 , F02K3/06 , F05D2260/4031 , Y02T50/671
Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing energy equal to less than about 2% of energy input into the gear system.
Abstract translation: 用于燃气涡轮发动机的风扇驱动齿轮系统包括在风扇驱动涡轮机和风扇之间提供减速的齿轮系统和齿轮系统的柔性支撑部分的安装件。 支持风扇驱动齿轮系统的润滑系统为齿轮系统提供润滑剂，并去除由齿轮系产生的热能。 润滑系统包括能量消除等于输入到齿轮系统中的能量的小于约2％的能量。
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公开(公告)号：US11225913B2
公开(公告)日：2022-01-18
申请号：US16186795
申请日：2018-11-12
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , William G. Sheridan
Abstract: A method is provided that includes providing a first turbine engine and providing a second turbine engine. The first turbine engine is configured with a first thrust rating. The first turbine engine includes a first engine rotating assembly and a first engine case structure housing at least the first engine rotating assembly. The second turbine engine is configured with a second thrust rating that is different than the first thrust rating. The second turbine engine includes a second engine rotating assembly and a second engine case structure housing at least the second engine rotating assembly. The first engine case structure and the second engine case structure have at least substantially common configurations. The first turbine engine and the second turbine engine are provided by a common entity.
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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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Patent Agency Ranking
公开(公告)号：US10808753B1
公开(公告)日：2020-10-20
申请号：US16429151
申请日：2019-06-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： William G. Sheridan , Todd A. Davis
Abstract: A method and an apparatus includes a static engine structure, at least one shaft that rotates relative to the static engine structure, and a bearing assembly that supports the shaft. The bearing assembly includes at least one first bearing hard mounted directly between the shaft and the static engine structure and at least one second bearing mounted between the shaft and the static engine structure. The at least one second bearing includes a damper. Also included is at least one third bearing that is mounted between the shaft and the static engine structure, wherein the at least one third bearing includes a resilient member.
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公开(公告)号：US10738646B2
公开(公告)日：2020-08-11
申请号：US15619799
申请日：2017-06-12
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
Abstract: A turbine engine has a fan and a low pressure compressor that rotate at a common speed and in a common direction. A fan drive turbine drives a gear reduction to, in turn, drive the low pressure compressor and the fan at a speed which is slower than a speed of the fan drive turbine. A combustor intermediate the low pressure compressor and the fan drive turbine and a thrust bearing mount the fan drive turbine, the thrust bearing being aft of a location of the combustor. A shear section in a drive connection connecting the fan drive turbine to the gear reduction is weaker than other portions of the drive connection. The shear section is aft of the thrust bearing.
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公开(公告)号：US20200217324A1
公开(公告)日：2020-07-09
申请号：US16825370
申请日：2020-03-20
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
IPC: F04D25/16 , F02C7/06 , F01D21/04 , F01D21/02 , F02C7/36 , F01D5/02 , F01D15/12 , F04D25/04 , F04D29/041 , F04D29/046 , F16H1/28 , F16H57/10
Abstract: A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.
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公开(公告)号：US10669948B2
公开(公告)日：2020-06-02
申请号：US15396870
申请日：2017-01-03
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
Abstract: A gas turbine engine comprises a fan drive turbine driving a shaft. The shaft engages a gear reduction. The gear reduction drives a fan rotor at a speed that is less than the speed of the fan drive turbine. The gear reduction is a non-epicyclic gear reduction.
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公开(公告)号：US10648383B2
公开(公告)日：2020-05-12
申请号：US15621406
申请日：2017-06-13
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , William G. Sheridan , Lawrence E. Portlock
IPC: F01D25/16 , F01N3/20 , F01D25/18 , F02C3/10 , F02K3/06 , F02C7/36 , F02C7/06 , F02C7/10 , F01N11/00 , F16N7/34
Abstract: A method of designing a gas turbine engine includes configuring a speed reduction device for driving a fan and configuring 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 the first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing is configured to also include 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.
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