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公开(公告)号：US20200256431A1
公开(公告)日：2020-08-13
申请号：US16274332
申请日：2019-02-13
Applicant: United Technologies Corporation
Inventor： Hung Duong , Marc J. Muldoon , Gabriel L. Suciu
Abstract: An auxiliary gearbox has a low speed input shaft driving a first plurality of accessories. A high speed input shaft drives a second plurality of accessories. The first plurality of accessories rotating about a first set of rotational axes, which are parallel to each other and perpendicular to a first plane. The second plurality of accessories rotating about a second set of rotational axes, which are parallel to each other and perpendicular to a second plane. The first and second planes extending in opposed directions away from a drive input axis of the high speed input shaft and the low speed input shaft. The low speed input shaft drives a variable speed transmission. A gas turbine engine is also disclosed.
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公开(公告)号：US20190242301A1
公开(公告)日：2019-08-08
申请号：US16390348
申请日：2019-04-22
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Marc J. Muldoon
CPC classification number: F02C7/06 , F01D5/02 , F02C3/04 , F02C7/36 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2260/40311 , F05D2260/98 , F16H57/0423 , F16H57/0427 , F16H57/0482 , F16H57/0486 , F16H57/082
Abstract: A gearbox assembly for a gas turbofan engine includes a sun gear rotatable about an axis and a plurality of intermediate gears driven by the sun gear. A baffle disposed between at least two of the plurality of intermediate gears includes a first gap distance within a first gap portion and a second gap distance within a second gap portion. The first gap portion is disposed between the baffle and one of the intermediate gears away from the meshed interface with the sun gear and the second gap portion is disposed near the interface with the sun gear. The first gap distance within the first gap portion is different than the second gap distance within the second gap portion to define a desired lubricant flow path.
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公开(公告)号：US10167734B2
公开(公告)日：2019-01-01
申请号：US14427679
申请日：2013-03-15
Applicant: United Technologies Corporation
Inventor： Masayoshi Sonokawa , Russell B. Witlicki , Christopher J. Larson , Robert C. Stutz , Eric Charles Mundell , Marc J. Muldoon
Abstract: A seal support and duct assembly of a gas turbine engine includes a seal support housing disposed about a central axis, a duct housing attached to the seal support housing, the duct housing and the seal support housing defining the seal support and duct assembly, an outer annular cavity, an inlet that supplies the outer annular cavity with cooling buffer air, an inner annular cavity disposed radially inward of the outer annular cavity, a first plurality of outlets that provide the cooling buffer air from the outer annular cavity to the inner annular cavity, and a second plurality of outlets that provide the cooling buffer air from the inner annular cavity to an area surrounding a bearing compartment.
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公开(公告)号：US10082203B2
公开(公告)日：2018-09-25
申请号：US15160881
申请日：2016-05-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Marc J. Muldoon
CPC classification number: F16H57/082 , F02K3/04 , F05D2220/36 , F05D2260/40311
Abstract: A gear carrier includes a first end plate. The gear carrier also includes a connector plate connected to the first end plate. The gear carrier also includes a second end plate. The gear carrier also includes a bushing configured to extend through the second end plate and into the connector plate to connect the second end plate to the connector plate.
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公开(公告)号：US09896969B2
公开(公告)日：2018-02-20
申请号：US14663207
申请日：2015-03-19
Applicant: United Technologies Corporation
Inventor： William G. Sheridan , Marc J. Muldoon , Michael E. McCune
CPC classification number: F01D25/186 , F01D11/02 , F01D25/166 , F01D25/183 , F05D2240/61 , F16H57/0426 , F16J15/164 , F16J15/42 , F16L27/087
Abstract: A transfer bearing assembly is configured to allow a flow of a fluid from an inlet tube to a channel defined by a rotating shaft. The transfer bearing assembly includes a body having an axially forward side and an axially aft side and a first wing having an axially aft end coupled to the axially forward side and an axially forward end. The transfer bearing assembly also includes a first side plate having a radially outward end coupled to the axially forward end of the first wing and a radially inward end.
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Patent Agency Ranking
公开(公告)号：US20160201793A1
公开(公告)日：2016-07-14
申请号：US14853208
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon
CPC classification number: F16H57/08 , F02C7/36 , F05D2260/40311 , F16C17/02 , F16H1/28 , F16H57/043 , F16H57/0479 , F16H57/0482 , F16H2057/085 , Y02T50/671
Abstract: An epicyclic gear system is provided. The gear system may comprise an annular gear centered about an axis, a star gear radially inward from the annular gear, a journal pin inside the star gear and comprising an internal bore with a recessed wall, and a sun gear radially inward from the star gear. A journal pin is also provided. The journal pin may include an internal bore formed along an axis of rotation of the journal pin, and a recessed wall of the internal bore with a diameter greater than the diameter of the internal bore.
Abstract translation: 提供行星齿轮系统。 齿轮系统可以包括以轴为中心的环形齿轮，从环形齿轮径向向内的星形齿轮，星形齿轮内的轴颈销，并且包括具有凹陷壁的内孔和从星形齿轮径向向内的太阳齿轮 。 还提供了一个日记销。 轴颈销可以包括沿着轴颈销的旋转轴线形成的内孔，以及具有大于内孔直径的内孔凹陷壁。
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公开(公告)号：US20150240660A1
公开(公告)日：2015-08-27
申请号：US14427679
申请日：2013-03-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Masayoshi Sonokawa , Russell B. Witlicki , Christopher J. Larson , Robert C. Stutz , Eric Charles Mundell , Marc J. Muldoon
CPC classification number: F01D25/125 , F01D25/08 , F01D25/12 , F01D25/14 , F01D25/16 , F01D25/162 , F01D25/24 , F02C7/06 , F02C7/18 , F05D2220/32 , F05D2240/50 , F05D2260/232 , Y02T50/675
Abstract: A seal support and duct assembly of a gas turbine engine includes a seal support housing disposed about a central axis, a duct housing attached to the seal support housing, the duct housing and the seal support housing defining the seal support and duct assembly, an outer annular cavity, an inlet that supplies the outer annular cavity with cooling buffer air, an inner annular cavity disposed radially inward of the outer annular cavity, a first plurality of outlets that provide the cooling buffer air from the outer annular cavity to the inner annular cavity, and a second plurality of outlets that provide the cooling buffer air from the inner annular cavity to an area surrounding a bearing compartment.
Abstract translation: 燃气涡轮发动机的密封支撑件和管道组件包括围绕中心轴线设置的密封支撑壳体，附接到密封件支撑壳体的管道壳体，管道壳体和限定密封件支撑件和管道组件的密封件支撑壳体， 环形空腔，为外部环形腔提供冷却缓冲空气的入口，设置在外部环形空腔的径向内侧的内部环形空腔;第一多个出口，其将冷却缓冲空气从外部环形空腔提供到内部环形腔 以及第二多个出口，其将冷却缓冲空气从内部环形空腔提供到围绕轴承隔室的区域。
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公开(公告)号：US11519289B2
公开(公告)日：2022-12-06
申请号：US16706058
申请日：2019-12-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Om P. Sharma , Joseph B. Staubach , Marc J. Muldoon , Jesse M. Chandler , David Lei Ma
Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.
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公开(公告)号：US11255263B2
公开(公告)日：2022-02-22
申请号：US16733504
申请日：2020-01-03
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon , Joseph B. Staubach , Jesse M. Chandler , Neil Terwilliger , Gabriel L. Suciu
Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.
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公开(公告)号：US20210239046A1
公开(公告)日：2021-08-05
申请号：US16782650
申请日：2020-02-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Marc J. Muldoon
Abstract: A cooling system for a plurality of conductive cables in a gas turbine engine includes a cooling source and an electric motor disposed in a tail cone. The cooling source may comprise an electric fan or an oil pump. The cooling source may be configured for active cooling of the plurality of conductive cables. The electric fan may be in fluid communication with ambient air during operation of the gas turbine engine.
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