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公开(公告)号：US20200025032A1
公开(公告)日：2020-01-23
申请号：US16298319
申请日：2019-03-11
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
IPC: F01D25/16 , F02C7/32 , F02C7/36 , F01D15/12 , F01D25/28 , F01D5/06 , F01D9/02 , F02K3/06 , F04D25/04 , F04D29/053 , F04D29/32 , F04D19/02 , F04D29/056
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 supports the fan shaft and defines a support transverse stiffness. A gear system is 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 gear system input is connected to the gear system and defines a gear system input lateral stiffness. A flexible support supports the gear system and defines a flexible support transverse stiffness. The gear system input lateral stiffness is less than 5% of the gear mesh lateral stiffness and 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：US10422243B2
公开(公告)日：2019-09-24
申请号：US15410049
申请日：2017-01-19
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Hung Duong , Jonathan F. Zimmitti , William G. Sheridan , Michael E. McCune , Brian Merry
IPC: F01D15/12 , F02C7/268 , F01D5/06 , F01D15/10 , F01D25/20 , F16H3/30 , F02C7/277 , F02C7/32 , F02C7/36
Abstract: An exemplary gas turbine engine assembly includes a transmission coupling a starter generator assembly to a first set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft.
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公开(公告)号：US10287915B2
公开(公告)日：2019-05-14
申请号：US14761241
申请日：2013-01-15
Applicant: United Technologies Corporation
Inventor： Michael E. McCune
Abstract: A turbine engine system includes a gutter and a gear train with an axial centerline. The gutter is disposed radially outside of the axial centerline. The gutter at least partially circumscribes the gear train, and includes an inner surface and a channel. The channel receives fluid directed out of the gear train. The channel extends radially into the gutter from the inner surface to a channel end, and circumferentially to a channel outlet. At least a portion of the channel has a cross-sectional channel geometry that tapers axially as the channel extends radially towards the channel end.
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公开(公告)号：US20190011033A1
公开(公告)日：2019-01-10
申请号：US16121929
申请日：2018-09-05
Applicant: United Technologies Corporation
Inventor： Michael E. McCune
IPC: F16H55/17 , F16H1/28 , B22F7/08 , B22F3/105 , B22F5/00 , F02C7/36 , B22F7/06 , B22F5/08 , B22F3/24
CPC classification number: F16H55/17 , B22F3/1055 , B22F5/009 , B22F5/085 , B22F7/064 , B22F7/08 , B22F2003/247 , F02C7/36 , F05D2260/40311 , F16H1/28 , Y02P10/295
Abstract: A gear includes a multiple of gear teeth that extend from an outer portion of a rim about an axis and an inner portion of the rim about the axis, the inner portion of the rim additive manufactured.
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公开(公告)号：US20180245518A1
公开(公告)日：2018-08-30
申请号：US15943812
申请日：2018-04-03
Applicant: United Technologies Corporation
Inventor： Michael E. McCune
CPC classification number: F02C7/36 , F01D15/12 , F02K3/04 , F02K3/072 , F05D2260/40311 , F16H1/28 , F16H1/46 , F16H57/0006 , Y02T50/671
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a compressor, a combustor, and a spool including a fan drive turbine that drives the fan through a gear reduction. The gear reduction includes at least two double helical gears in meshed engagement, each of the at least two double helical gears having a first plurality of gear teeth separated from a second plurality of gear teeth such that a first end of the first plurality of gear teeth and a first end of the second plurality of gear teeth are spaced apart by an axial distance. Each of the first plurality of gear teeth is offset a first circumferential offset distance in relation to the next gear tooth of the second plurality of gear teeth when moving in a circumferential direction relative to respective axes.
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Patent Agency Ranking
公开(公告)号：US20180216531A1
公开(公告)日：2018-08-02
申请号：US15418933
申请日：2017-01-30
Applicant: United Technologies Corporation
Inventor： Michael E. McCune
CPC classification number: F02C7/06 , F02C3/04 , F02C7/36 , F02K3/06 , F05D2220/32 , F05D2240/35 , F05D2260/40311 , F05D2260/98 , F16H1/28 , F16H57/04 , F16H57/0426 , F16H57/043 , F16H57/0479 , F16H57/0486 , F16H57/08 , F16H2057/085
Abstract: An epicyclic gear system includes a sun gear, a ring gear, and two or more star gear assemblies enmeshed between the sun gear and the ring gear. Each star gear assembly includes a star gear and a journal bearing supportive of the star gear. The journal bearing includes one or more lubricant passageways to deliver a flow of lubricant to a selected location of the star gear assembly, wherein a first cross-sectional area of a lubricant passage of a first journal bearing of the two or more star gear assemblies is greater than a second cross-sectional area of the corresponding lubricant passage of a second journal bearing of the two or more star gear assemblies.
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公开(公告)号：US09951860B2
公开(公告)日：2018-04-24
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：US20180094532A1
公开(公告)日：2018-04-05
申请号：US15816512
申请日：2017-11-17
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 fan shaft that has fan blades. A fan shaft is drivingly connected to the fan. A fan shaft support supports the fan shaft and defines a fan shaft support lateral stiffness. A gear system is connected to the fan shaft and driven through an input. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the input during operation and includes a flexible support that defines a flexible support lateral stiffness that is less than 11% of the shaft support lateral stiffness.
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公开(公告)号：US20180087654A1
公开(公告)日：2018-03-29
申请号：US15808613
申请日：2017-11-09
Applicant: United Technologies Corporation
Inventor： William P. 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 turbo fan engine includes a housing that supports a compressor section. At least one compressor hub is within the compressor section. A compressor shaft is arranged in the compressor section. An epicyclic gear train is coupled to the compressor shaft. At least one compressor hub and the compressor shaft are coupled at a common attachment point. The epicyclic gear train includes a carrier. A sun gear and intermediate gears are 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.
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公开(公告)号：US20180080476A1
公开(公告)日：2018-03-22
申请号：US15269342
申请日：2016-09-19
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Gabriel L. Suciu
IPC: F04D29/58 , F04D29/54 , F04D29/52 , F04D29/063
CPC classification number: F04D29/5853 , F01D9/06 , F02C7/06 , F02C7/14 , F02C7/18 , F02C7/24 , F02K3/06 , F04D29/063 , F04D29/522 , F04D29/542 , F05D2240/15 , F05D2260/231 , F05D2260/40311
Abstract: An assembly for use in a gas turbine engine includes a center body support section including inner and outer annular walls, a plurality of struts, and a heat shield. The outer annular wall is disposed radially outward of the inner annular wall and a plurality of struts connect the inner and outer annular walls. The heat shield is disposed radially inward of and connected to the inner annular wall, such that a cavity is formed between the heat shield and the inner annular wall. The cavity is open to an air flow at a forward face of the center body support section. The inner annular wall and heat shield include first and second forward edges, respectively. The first and second forward edges are aligned axially.
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