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公开(公告)号：US20150361880A1
公开(公告)日：2015-12-17
申请号：US14600487
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Wesley K. Lord , Jesse M. Chandler , Michael Winter , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机包括多个风扇转子。 气体发生器包括至少一个压缩机转子，至少一个气体发生器涡轮机转子，燃烧部分和在至少一个气体发生器涡轮机转子下游的风扇驱动涡轮机。 轴构造成由风扇驱动涡轮机驱动。 轴接合齿轮以驱动多个风扇转子。 系统控制提供给多个风扇转子的功率量。 还公开了一种操作燃气涡轮发动机的方法。
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公开(公告)号：US20150274306A1
公开(公告)日：2015-10-01
申请号：US14620259
申请日：2015-02-12
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
CPC classification number: B64D27/24 , B64D35/02 , B64D35/04 , B64D2027/026 , F01D15/12 , F02C7/36 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312 , F05D2260/4023 , F05D2260/4031 , Y02T50/62 , Y10S903/903
Abstract: A gas turbine engine has a fan drive turbine for selectively driving a fan rotor. A drive shaft between the fan drive turbine and the fan rotor includes a clutch, and an electric motor. The electric motor is positioned such that it is not downstream of a flow path relative to the fan drive turbine. A method of operating a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机具有用于选择性地驱动风扇转子的风扇驱动涡轮机。 风扇驱动涡轮机和风扇转子之间的驱动轴包括离合器和电动机。 电动机被定位成使得其不相对于风扇驱动涡轮机的流动路径的下游。 还公开了一种操作燃气涡轮发动机的方法。
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公开(公告)号：US20140369818A1
公开(公告)日：2014-12-18
申请号：US14474869
申请日：2014-09-02
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: 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 and a second race. A second bearing for rotation is within the first bearing including 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. There is a rotating carrier for supporting at least one planetary gear. The second bearing extends from the rotating carrier about an axis. A first spray bar is disposed on the carrier. The second bearing has a second opening in registration with the second race and a second conduit for passing lubricant to the spray bar.
Abstract translation: 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和第二种族。 用于旋转的第二轴承在第一轴承内，包括与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。 存在用于支撑至少一个行星齿轮的旋转载体。 第二轴承围绕轴线从旋转载体延伸。 第一喷杆设置在载体上。 第二轴承具有与第二座圈对准的第二开口和用于将润滑剂传送到喷杆的第二导管。
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44.发明申请公开(公告)号：US20140274531A1
公开(公告)日：2014-09-18
申请号：US14290576
申请日：2014-05-29
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
CPC classification number: F16H1/28 , F01D25/16 , F02C7/36 , F16C23/045 , F16C2360/23 , F16H57/0427 , F16H57/082 , Y02T50/672 , Y10T29/49245
Abstract: A fan gear drive system includes a fan shaft, a turbine shaft, a fixed structure, and a gear train which includes a torque frame that comprises a base with integrated gear shafts that are circumferentially spaced relative to one another. Each shaft provides a shaft axis. Intermediate gears are supported on each bearing assembly for rotation about the bearing axis. A central gear is located radially inward from and intermeshes with the intermediate gears. A ring gear is arranged about and intermeshes with the intermediate gears. One of the torque frame, central gear and ring gear is connected to the fan shaft. Another of the torque frame, central gear and ring gear is connected to the turbine shaft. The remaining of the torque frame, central gear and ring gear is connected to the fixed structure. A bearing assembly is mounted on each of the gear shafts and provides a bearing axis. Each bearing assembly supports the respective intermediate gear.
Abstract translation: 风扇齿轮传动系统包括风扇轴，涡轮轴，固定结构和齿轮系，其包括扭矩框架，该扭矩框架包括具有相对于彼此周向间隔开的一体化齿轮轴的基座。 每个轴提供轴轴。 中间齿轮支撑在每个轴承组件上以围绕轴承轴线旋转。 中心齿轮径向向内定位并与中间齿轮相互啮合。 环形齿轮布置在中间齿轮周围并与之啮合。 扭矩框架，中心齿轮和环形齿轮之一连接到风扇轴。 扭矩框架，中心齿轮和环形齿轮中的另一个连接到涡轮轴。 扭矩框架，中心齿轮和环形齿轮的剩余部分连接到固定结构。 轴承组件安装在每个齿轮轴上并提供轴承轴线。 每个轴承组件支撑相应的中间齿轮。
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45.发明授权Method for setting a gear ratio of a fan drive gear system of a gas turbine engine 有权用于设定燃气轮机的风扇驱动齿轮系的齿轮比的方法公开(公告)号：US08814494B1
公开(公告)日：2014-08-26
申请号：US14203863
申请日：2014-03-11
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Karl L. Hasel
CPC classification number: F02C7/36 , F05D2230/60 , F05D2260/40311 , F05D2260/941
Abstract: A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0.
Abstract translation: 燃气涡轮发动机包括风扇部分，风扇部分包括可围绕轴线旋转的风扇。 减速装置连接到风扇。 减速装置包括具有至少2.5的行星齿轮比的行星风扇驱动齿轮系统。 旁路比大于约11.0。
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Patent Agency Ranking
公开(公告)号：US20140227084A1
公开(公告)日：2014-08-14
申请号：US14170687
申请日：2014-02-03
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
CPC classification number: F02C7/36 , F05D2220/327 , F05D2260/40311 , F16H1/227 , F16H1/46
Abstract: A compound star gear system includes a sun gear rotatable about a first axis that drives a first plurality of star gears rotatable about a plurality of fixed axes. The first plurality of star gears drives a second plurality of star gears spaced axially apart from the first plurality of star gears. The second plurality of star gears drive the ring gear that in turn drives a fan drive shaft.
Abstract translation: 复合星形齿轮系统包括可围绕第一轴线旋转的太阳齿轮，所述第一轴线驱动围绕多个固定轴线可旋转的第一多个星形齿轮。 第一多个星形齿轮驱动与第一多个星形齿轮轴向分开的第二多个星形齿轮。 第二个多个星形齿轮驱动齿圈，从而驱动风扇驱动轴。
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公开(公告)号：US08756908B2
公开(公告)日：2014-06-24
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：US08667688B2
公开(公告)日：2014-03-11
申请号：US13629834
申请日：2012-09-28
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , William G. Sheridan
CPC classification number: F02C7/36 , F02C3/107 , F02C7/32 , F02K3/06 , F05D2230/60 , F05D2260/40311 , F16H1/28 , F16H57/023 , F16H57/0423 , F16H57/0456 , F16H57/0479 , F16H57/0486 , F16H57/082 , Y02T50/671 , Y10T29/49464
Abstract: A method of assembling an epicyclic gear train includes the steps of providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced apart apertures provided at an outer circumference of the carrier. Gear pockets are provided between the walls and extend to the apertures, and a central opening in at least one of the walls. A plurality of intermediate gears is inserted through the central opening and move the intermediate gears radially outwardly into the gear pockets to extend through the apertures. A sun gear is inserted through the central opening. The plurality of intermediate gears is moved radially inwardly to engage the sun gear. A gear reduction is also disclosed.
Abstract translation: 一种组装行星齿轮系的方法包括以下步骤：提供具有中心轴线的整体载体，该中心轴线包括设置在载体的外圆周处的间隔开的壁和周向间隔开的孔。 齿轮槽设置在壁之间并延伸到孔，以及在至少一个壁中的中心开口。 多个中间齿轮通过中心开口插入并将中间齿轮径向向外移动到齿轮槽中以延伸穿过孔。 太阳齿轮穿过中央开口插入。 多个中间齿轮径向向内移动以接合太阳齿轮。 还公开了齿轮减速。
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公开(公告)号：US11300057B2
公开(公告)日：2022-04-12
申请号：US15981559
申请日：2018-05-16
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
IPC: F02C7/36 , F02K3/04 , F16D41/069 , F16H1/20
Abstract: A gas turbine engine including a fan and an oil pump operatively connected to the fan by a main input drive gear, the drive gear rotating when the fan rotor rotates in either a first or second direction of the fan. Further included is a gear train intermediate the main input drive gear and the oil pump, the gear train including a first and second pinion gear, the first and second pinion gear each driven by the main input drive gear, the first pinion gear driving a first gear through a first clutch, the second pinion gear driving a second gear through a second clutch. Only one of the clutches transmits rotation from the respective pinion gear to the respective gear when the fan is rotating in the first direction, with the only the other clutch transmitting rotation when the fan is rotating in the second direction.
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公开(公告)号：US11125167B2
公开(公告)日：2021-09-21
申请号：US16291392
申请日：2019-03-04
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
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.
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