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公开(公告)号：US20200256430A1
公开(公告)日：2020-08-13
申请号：US16274360
申请日：2019-02-13
Applicant: United Technologies Corporation
Inventor： Hung Duong , Marc J. Muldoon , Gabriel L. Suciu , Joseph H. Polly , Nicholas D. Leque
Abstract: A gas turbine engine includes a low speed input shaft connected to a low speed tower shaft, in turn connected to a lower speed spool and a high speed input connected to a high speed tower shaft, in turn connected to a higher speed spool. The low speed input shaft is connected to drive a first plurality of accessories. The high speed input shaft is connected to drive a second plurality of accessories. The high speed tower shaft and the low speed tower shaft are coaxial and rotate about a common axis. An angle drive is provided into the low speed input shaft and the high speed input shaft, respectively.
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公开(公告)号：US20200256258A1
公开(公告)日：2020-08-13
申请号：US16274340
申请日：2019-02-13
Applicant: United Technologies Corporation
Inventor： Hung Duong , Marc J. Muldoon , Gabriel L. Suciu
Abstract: A gas turbine engine has a low speed input shaft drives 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 perpendicular to a first plane. The second plurality of accessories rotating about a second set rotational axes perpendicular to a second plane. The first and second planes extending in opposed directions away from a drive input axis. Compressed air is tapped and passes through a heat exchanger, then to a boost compressor, and then to at least one rotatable components in a main compressor section and a main turbine section. The boost compressor driven on a boost axis, which is non-parallel to the first set of rotational axes and the second set of rotational axes.
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公开(公告)号：US20190382112A1
公开(公告)日：2019-12-19
申请号：US16012027
申请日：2018-06-19
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon
Abstract: A method of operating an aircraft according to an exemplary embodiment of this disclosure includes, among other possible things, communicating power from a storage device within an unmoved aerial vehicle (UAV) to an aircraft; controlling a propulsive device within the UAV with a control system of the aircraft to provide propulsive thrust to the aircraft; and detaching the UAV including the storage device and the propulsion device from the aircraft responsive to the energy within the storage device being below a predefined threshold.
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公开(公告)号：US20190316523A1
公开(公告)日：2019-10-17
申请号：US16431050
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon
Abstract: A turbofan engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan drive gear system including a carrier for supporting a plurality of gears, and a scupper capturing lubricant during gear operation and directing lubricant into the carrier. A fan drive gear system is also disclosed.
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公开(公告)号：US10267232B2
公开(公告)日：2019-04-23
申请号：US14763535
申请日：2014-01-24
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Marc J. Muldoon
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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Patent Agency Ranking
公开(公告)号：US20160069212A1
公开(公告)日：2016-03-10
申请号：US14831963
申请日：2015-08-21
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Marc J. Muldoon
CPC classification number: F01D25/18 , F01D25/16 , F02C7/06 , F05D2220/32 , F05D2240/50 , F05D2260/40311 , F05D2260/98 , F16C33/1045 , F16C33/106 , F16H57/043 , F16H57/0479 , F16H57/0482 , Y02T50/671
Abstract: A transfer bearing assembly includes a transfer bearing shaft. An oil transfer bearing surrounds the transfer bearing shaft. A radially extending tube is attached to the transfer bearing shaft and is configured to engage a carrier on a speed reduction device.
Abstract translation: 转印轴承组件包括转印轴承轴。 输油轴承围绕转印轴承轴。 径向延伸的管附接到传送轴承轴并且构造成与减速装置上的载体接合。
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公开(公告)号：US20150052873A1
公开(公告)日：2015-02-26
申请号：US14510644
申请日：2014-10-09
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon
CPC classification number: F02C7/06 , F02C3/04 , F02C7/36 , F05D2260/40311 , F05D2260/609 , F05D2260/98 , F16H57/0431 , F16H57/0482
Abstract: A turbofan engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, a fan drive gear system including a carrier for supporting a plurality of gears, and a scupper capturing lubricant during gear operation and directing lubricant into the carrier. A fan drive gear system is also disclosed.
Abstract translation: 涡轮风扇发动机包括可围绕轴线旋转的风扇，压缩机部分，与压缩机部分流体连通的燃烧器，与燃烧器流体连通的涡轮部分，包括用于支撑多个齿轮的载体的风扇驱动齿轮系统， 以及在齿轮操作期间捕获润滑剂并将润滑剂引导到载体中的沉淀器。 还公开了一种风扇驱动齿轮系统。
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公开(公告)号：US11346427B2
公开(公告)日：2022-05-31
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：US20210207530A1
公开(公告)日：2021-07-08
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
IPC: F02C6/20
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：US20200300164A1
公开(公告)日：2020-09-24
申请号：US16744508
申请日：2020-01-16
Applicant: United Technologies Corporation
Inventor： Marc J. Muldoon , Melissa B. Chapin
IPC: F02C7/14
Abstract: An aircraft includes at least one gas turbine engine connected to a wing via an engine pylon. The gas turbine engine includes an engine core having a compressor section, a combustor section, and a turbine section and at least one actively cooled engine system. A fan is disposed fore of the engine core and is rotatably connected to the engine core via a shaft. The engine pylon is disposed within a bifurcation and intersects a fan stream of the fan. The engine pylon includes a pylon space. At least one heat exchanger is disposed within the pylon space. The heat exchanger includes a first inlet connected to the at least one actively cooled engine system and a first outlet connected to the at least one actively cooled engine system.
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