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公开(公告)号：US20170306852A1
公开(公告)日：2017-10-26
申请号：US15137614
申请日：2016-04-25
Applicant: United Technologies Corporation
Inventor： Paul Attridge , Gabriel L. Suciu , Kurt J. Sobanski , Jesse M. Chandler
CPC classification number: F02C7/32 , B64C27/625 , B64C27/64 , B64C27/68 , B64C33/00 , F02C3/04 , F02C7/20 , F02C7/25 , F02C7/36 , F02K3/06 , F05D2260/57 , F05D2270/62 , H02K7/003 , H02K11/20
Abstract: An electromechanical system for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine, and an electrical motor located at a second side of the firewall and configured to drive the mechanical component. The electrical motor mechanically connected to the mechanical component through a firewall opening in the firewall, the first side having a higher operating temperature than the second side. An electrical connection extends between the mechanical component and the electrical motor via the same firewall opening.
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公开(公告)号：US20170306847A1
公开(公告)日：2017-10-26
申请号：US15138269
申请日：2016-04-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. A second tap taps air from the compressor section, passes the air across a cabin air pump, and delivers air from the cabin air pump for use on an aircraft receiving the gas turbine engine. The cooling compressor including a rotor, and the cabin air pump including a rotor, and a drive driven with the turbine section in turn drives both the cooling compressor rotor and the cabin air supply rotor. A combined intercooling system and cabin air supply system is also disclosed.
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公开(公告)号：US20170276012A1
公开(公告)日：2017-09-28
申请号：US15079400
申请日：2016-03-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jesse M. Chandler , Gabriel L. Suciu , Joseph Stack
CPC classification number: F01D17/162 , F01D9/04 , F01D9/041 , F01D9/042 , F01D17/105 , F01D17/12 , F01D17/14 , F01D17/16 , F01D25/34 , F02K3/02 , F05D2220/323 , F05D2260/40 , Y02T50/671 , Y02T50/673
Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.
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公开(公告)号：US09695778B2
公开(公告)日：2017-07-04
申请号：US14184398
申请日：2014-02-19
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
Abstract: One embodiment includes a pivot thrust reverser comprising a first tandem pivot door subassembly comprising an inner panel and outer panel connected. A second tandem pivot door subassembly is included comprising an inner panel and outer panel connected. Also included are a first actuator located on a first side of an attachment location to pivot the first tandem pivot door subassembly, a second actuator located on a second side of the attachment location to pivot the second tandem pivot door subassembly, and a third actuator located substantially radially opposite the attachment location to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly. The first tandem pivot door is configured to be pivoted from stowed to deployed by the first actuator and the third actuator, and the second tandem pivot door is configured to be pivoted from stowed to deployed by the second actuator and the third actuator.
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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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Patent Agency Ranking
公开(公告)号：US20170122207A1
公开(公告)日：2017-05-04
申请号：US14932066
申请日：2015-11-04
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02C7/14 , B64C11/14 , F01D5/12 , F01D9/041 , F02C3/04 , F02C7/18 , F02K3/06 , F05D2220/32 , F05D2240/35 , F05D2260/213
Abstract: A gas turbine engine has a nose cone, a fan for delivering air into a bypass duct as bypass flow, and into a core engine to be delivered to a compressor. The nose cone includes a vent to receive air and deliver the air across a heat exchanger, which receives a fluid to be cooled. The air from the vents is delivered to an outlet downstream of the heat exchanger, such that a majority of the air being delivered to the outlet becomes part of the bypass flow.
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公开(公告)号：US09631578B2
公开(公告)日：2017-04-25
申请号：US14184313
申请日：2014-02-19
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , T. David Bomzer
CPC classification number: F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
Abstract: A pivot thrust reverser includes a first pivot door forming a first portion of a nacelle when stowed and second pivot door forming a second portion of the nacelle when stowed. The first pivot door and second pivot door each form a portion of a surface of a bypass duct when in a stowed position. In the deployed position the first pivot door and the second pivot door circumferentially surround a portion of an inner surface of a bypass duct such that when the pivot thrust reverser is deployed during engine operation a fan bypass stream is redirected while both a core stream and a nacelle ventilation stream flow in substantially the same manner as when the pivot thrust reverser is stowed.
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公开(公告)号：US20170096232A1
公开(公告)日：2017-04-06
申请号：US14874560
申请日：2015-10-05
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Wesley K. Lord , Alan H. Epstein , Steven M. O'Flarity
Abstract: A drive arrangement for an aircraft comprises a pair of propulsor units each having a fan and a fan shaft for driving the fan. A core engine has a turbine driving a core engine shaft. A mechanical connection connects the core engine shaft to drive the fan shafts for each of the propulsor units An aircraft is also disclosed.
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公开(公告)号：US20160312797A1
公开(公告)日：2016-10-27
申请号：US14695534
申请日：2015-04-24
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry
CPC classification number: F04D29/5826 , F01D25/12 , F02C3/13 , F02C6/08 , F02C7/143 , F02C7/185 , F02C9/18 , F04D29/5833 , F05D2220/3212 , F05D2220/3217 , F05D2220/3219 , F05D2260/211 , F05D2260/213 , F05D2260/606 , F05D2270/3062 , Y02T50/675
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.
Abstract translation: 燃气涡轮发动机包括具有下游最末端的高压压缩机和更上游位置的主压缩机部分。 涡轮机部分具有高压涡轮机。 第一分接头从主压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。 冷却压缩机压缩热交换器下游的空气。 第二分接头从距离第一抽头的位置更靠近下游最端的位置敲击空气。 第一和第二抽头混合在一起并被输送到高压涡轮。 还公开了一种用于燃气涡轮发动机的中间冷却系统。
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公开(公告)号：US09435293B2
公开(公告)日：2016-09-06
申请号：US14187027
申请日：2014-02-21
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , T. David Bomzer
CPC classification number: F02K1/605 , F01D25/24 , F02C3/04 , F02K1/60 , F02K1/62 , F02K1/625 , F02K1/64 , F02K1/70 , F02K1/72 , F02K1/763 , F02K1/766 , F05D2220/32 , F05D2230/72 , F05D2240/14 , F05D2270/051
Abstract: A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.
Abstract translation: 燃气涡轮发动机包括静止的第一环形部分，并适于部分地围绕发动机芯。 第一环形部分包括前挂架连接部分。 燃气涡轮发动机还包括连接到前挂架并沿着后方向从第一环形部分延伸的轨道。 燃气涡轮发动机还包括第二环形部分，其布置在第一部分的后部并且联接到轨道。 第二环形部分可沿着发动机芯心中心线在关闭位置和至少一个打开位置之间移动。 第二环形部分构造成在关闭位置接合第一环形部分，从而提供对发动机芯的通路。 燃气涡轮发动机还包括布置在第二环形部分中的推力反向器。
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