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公开(公告)号：US09777825B2
公开(公告)日：2017-10-03
申请号：US14455539
申请日：2014-08-08
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 turbine engine includes a housing supporting compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. 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 at least one of the sun gear and the intermediate gears. A spray bar is external to the carrier and is in communication with the lubrication passage. The spray bar terminates near the sun gear for directing lubricant on the sun gear.
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公开(公告)号：US20170276046A1
公开(公告)日：2017-09-28
申请号：US15621406
申请日：2017-06-13
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 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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公开(公告)号：US20170276009A1
公开(公告)日：2017-09-28
申请号：US15606386
申请日：2017-05-26
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 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 said that supports fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear lateral stiffness and a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral stiffness and the ring gear transverse stiffness is less than 12% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.
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公开(公告)号：US20170218850A1
公开(公告)日：2017-08-03
申请号：US15485563
申请日：2017-04-12
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 defined 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 between 0.5 and 1.5.
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公开(公告)号：US20170218789A1
公开(公告)日：2017-08-03
申请号：US15485512
申请日：2017-04-12
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 defined 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 between 0.5 and 1.5.
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Patent Agency Ranking
公开(公告)号：US20170152756A1
公开(公告)日：2017-06-01
申请号：US14935673
申请日：2015-12-01
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , William G. Sheridan , Michael E. McCune , Gabriel L. Suciu
CPC classification number: F01D15/12 , F01D25/18 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/50 , F05D2260/40311 , F05D2260/98 , F16H1/28 , F16H57/0479 , F16H57/0486
Abstract: A gas turbine engine has a fan rotor, a turbine rotor driving the fan rotor, and an epicyclic gear reduction positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and no more than four intermediate gears that engage the sun gear and the ring gear. The fan drive turbine is configured to drive the sun gear to, in turn, drive the ring gears to, in turn, drive the fan rotor.
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公开(公告)号：US09650954B2
公开(公告)日：2017-05-16
申请号：US14597510
申请日：2015-01-15
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Michael E. McCune , Jesse M. Chandler , Alan H. Epstein , Steven M. O'Flarity , Christopher J. Hanlon , William F. Schneider , Joseph B. Staubach , James A. Kenyon
IPC: F02C3/107 , B64D35/04 , F01D13/00 , F02K3/077 , F02C7/36 , F02C3/06 , F02C3/067 , F02C9/18 , B64D27/18
CPC classification number: F02C3/107 , B64D27/18 , B64D35/04 , F01D13/003 , F02C3/06 , F02C3/067 , F02C7/36 , F02C9/18 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312
Abstract: A gas generator has at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine is positioned downstream of a path of the products of combustion having passed over the at least one gas generator turbine rotor. The fan drive turbine drives a shaft and the shaft engages gears to drive at least three fan rotors.
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公开(公告)号：US09631558B2
公开(公告)日：2017-04-25
申请号：US13908177
申请日：2013-06-03
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 flex mount for a fan drive gear system. A very high speed fan drive turbine drives the fan drive gear system.
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公开(公告)号：US20170089448A1
公开(公告)日：2017-03-30
申请号：US15380570
申请日：2016-12-15
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：US09476321B2
公开(公告)日：2016-10-25
申请号：US13741469
申请日：2013-01-15
Applicant: United Technologies Corporation
Inventor： Tony Haugh , Michael E. McCune , James B. Coffin
CPC classification number: F01D25/18 , F02C7/14 , Y02T50/675
Abstract: An example turbomachine fluid delivery manifold provides a journal fluid path and a gear mesh fluid path that is separate from the journal fluid path. An example turbomachine lubrication system includes a geared architecture having a journal bearing and a gear. In this example, a manifold provides a portion of a first fluid path and a portion of a second fluid path separate from the first fluid path. The first fluid path is operative to communicate a first fluid from a fluid supply to the journal bearing. The second fluid path is operative to communicate a second fluid from the fluid supply to a gear mesh.
Abstract translation: 示例性的涡轮机输送歧管提供了一个轴颈流体路径和与轴颈流体路径分开的齿轮啮合流体路径。 示例性涡轮机润滑系统包括具有轴颈轴承和齿轮的齿轮架构。 在该示例中，歧管提供第一流体路径的一部分和与第一流体路径分离的第二流体路径的一部分。 第一流体路径用于将来自流体供应的第一流体传送到轴颈轴承。 第二流体路径用于将来自流体供应的第二流体传递到齿轮网。
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