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公开(公告)号：US09874274B2
公开(公告)日：2018-01-23
申请号：US14485039
申请日：2014-09-12
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Michael E. McCune
CPC classification number: F16H57/0427 , F01D25/18 , F02C3/04 , F02C7/36 , F05D2230/60 , F05D2260/40311 , F05D2260/98 , F16H57/0421 , F16H57/0423 , F16H57/046 , F16H57/0479 , F16H57/0482 , F16H57/0486 , F16H57/082 , Y10T29/49316 , Y10T29/4932 , Y10T29/49323 , Y10T29/49464
Abstract: A geared architecture includes a carrier that has spaced apart walls with circumferentially spaced mounts that interconnect the walls. The mounts provide circumferentially spaced apart apertures between the mounts at an outer circumference of the carrier. A sun gear and intermediate gears are arranged about and intermesh with the sun gear. The intermediate gears are supported by the carrier. The intermediate gears extend through the apertures to intermesh with a ring gear. A baffle is supported relative to the carrier and includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on the at least one of the sun gear and intermediate gears. The lubrication passage includes a primary passage that extends laterally between the walls and first and second passages and is in communication with the primary passage and respectively terminates near the sun gear and intermediate gears.
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公开(公告)号：US09874150B2
公开(公告)日：2018-01-23
申请号：US14222919
申请日：2014-03-24
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 comprises the steps of providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced connecting structure defining spaced apart apertures provided at an outer circumference of the carrier. Gear pockets are provided between the walls and extend to the apertures. A central opening is in at least one of the walls. A plurality of intermediate gears are inserted through the central opening and move the intermediate gears radially outwardly into the gear pockets to extend into 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.
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公开(公告)号：US20180010681A1
公开(公告)日：2018-01-11
申请号：US15691259
申请日：2017-08-30
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: An epicyclic gear train for a turbine engine includes a gutter with an annular channel. A rotating structure includes a ring gear that has an aperture that is axially aligned with the annular channel. Axially spaced apart walls extend radially outward relative to the rotating structure to define a passageway. The passageway is arranged radially between and axially aligned with the aperture and the annular channel. The walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel.
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公开(公告)号：US20170260875A1
公开(公告)日：2017-09-14
申请号：US15606556
申请日：2017-05-26
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
CPC classification number: F01D25/164 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/16 , F01D25/28 , F02C7/32 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/045 , F04D29/053 , F04D29/056 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/60 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y10T29/49321
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support that supports the fan shaft and defines a fan shaft support transverse stiffness. A gear system connected to the fan shaft and includes a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. A flexible support supports said gear system and defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 20% of the fan shaft support transverse stiffness.
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公开(公告)号：US09752511B2
公开(公告)日：2017-09-05
申请号：US15484441
申请日：2017-04-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.
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Patent Agency Ranking
公开(公告)号：US09752510B2
公开(公告)日：2017-09-05
申请号：US15000077
申请日：2016-01-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Alan H. Epstein , Wesley K. Lord , Michael E. McCune , Brian D. Merry
CPC classification number: F02C7/36 , F01D15/12 , F02C3/06 , F02C3/107 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2240/60 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.
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公开(公告)号：US20170175874A1
公开(公告)日：2017-06-22
申请号：US14976166
申请日：2015-12-21
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Michael E. McCune
CPC classification number: F16H57/0435 , F01D21/00 , F01D25/20 , F02C3/107 , F02C7/06 , F02C7/36 , F05D2220/76 , F05D2230/72 , F05D2260/4031 , F05D2260/40311 , F05D2260/98 , F05D2270/304 , F16H57/0434 , F16H57/045 , F16H57/0471 , F16H57/0479
Abstract: A gas turbine engine installed on an aircraft includes a fan rotor, a turbine rotor, a gearbox, an auxiliary pump, and an electric motor. The gearbox couples the fan rotor to the turbine rotor, the turbine rotor being adapted to drive the fan rotor via the gearbox. The auxiliary pump is configured to circulate lubricating fluid in an auxiliary lubrication system and supplies the gearbox. The electric motor is configured to receive electricity when the aircraft is parked an adapted to drive the auxiliary pump such that the auxiliary pump circulates lubricating fluid while the aircraft is parked.
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公开(公告)号：US20170175581A1
公开(公告)日：2017-06-22
申请号：US15451929
申请日：2017-03-07
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
IPC: F01D25/16 , F04D29/053 , F04D25/04 , F01D5/06 , F04D29/056 , F01D9/02 , F02K3/06 , F02C7/36 , F04D19/02 , F04D29/32 , F01D15/12
CPC classification number: F01D25/164 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/16 , F01D25/28 , F02C7/32 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/045 , F04D29/053 , F04D29/056 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/60 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y10T29/49321
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. The ring gear transverse stiffness is less than 20% of the gear mesh transverse stiffness.
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公开(公告)号：US20170122330A1
公开(公告)日：2017-05-04
申请号：US14927108
申请日：2015-10-29
Applicant: United Technologies Corporation
Inventor： JACOB PETER MASTRO , Michael E. McCune
CPC classification number: F04D29/061 , B64D27/16 , F01D21/045 , F01D25/20 , F02C7/32 , F02K3/04 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/323 , F05D2220/36 , F16H57/04 , F16H57/0436 , F16H57/0471
Abstract: What is described is a system for pumping lubricant to a component of a gas turbine engine. The system includes a fan gear coupled to a fan shaft of the gas turbine engine and configured to rotate in a forward direction and in a reverse direction based at least partially on a direction of wind relative to a fan of the gas turbine engine. The system also includes a first pump coupled to the fan gear and configured to pump lubricant to the component in response to the fan rotating in the forward direction. The system also includes a second pump coupled to the fan gear and configured to pump lubricant to the component in response to the fan rotating in the reverse direction.
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公开(公告)号：US20160138422A1
公开(公告)日：2016-05-19
申请号：US15007296
申请日：2016-01-27
Applicant: United Technologies Corporation
Inventor： James B. Coffin , Michael E. McCune , William G. Sheridan
IPC: F01D25/18 , F16H57/025
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 exemplary method of lubricating a turbomachine interface includes, among other things, securing a carrier relative to a torque frame using a flexure pin, and lubricating an interface of the flexure pin using a lubricant that has moved through a lubricant passage in the carrier and a lubricant passage in the flexure pin.
Abstract translation: 润滑涡轮机接口的示例性方法包括：使用弯曲销固定载体相对于扭矩框架的载体;以及使用已经移动通过载体中的润滑剂通道的润滑剂润滑挠曲销的界面，以及 柔性销中的润滑剂通道。
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