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公开(公告)号：US10094281B2
公开(公告)日：2018-10-09
申请号：US14595284
申请日：2015-01-13
Applicant: United Technologies Corporation
Inventor： Jesse M. Chandler , Gabriel L. Suciu
Abstract: A gas turbine engine comprises a fan on an engine central axis. Plural gas generators are downstream of the fan, each along a respective central axis, mutually offset, and offset from the engine central axis. A fan drive turbine is on the engine central axis, downstream of the dual gas generators, and driven by output from the dual gas generators, to drive the fan.
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公开(公告)号：US20180163633A1
公开(公告)日：2018-06-14
申请号：US15373072
申请日：2016-12-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A propulsion system for an aircraft has at least two fans with each fan having a fan drive shaft. A turboshaft gas turbine engine drives each of the at least two fans. The turboshaft engine drives an output shaft which drives a gear to, in turn, engage to drive a gear on a first intermediate shaft extending from the turboshaft gas turbine engine in a rearward direction toward an intermediate fan drive shaft. The intermediate fan drive shaft drives the fan drive shaft, and the at least two first intermediate drive shafts extending over a distance that is greater in an axial dimension defined between the turboshaft gas turbine engine and the fan than it is in a width dimension defined between the at least two fans.
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公开(公告)号：US09982599B2
公开(公告)日：2018-05-29
申请号：US14443145
申请日：2013-06-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02C7/052 , B01D46/0023 , F02C7/12 , F05D2220/327 , F05D2260/40311 , F05D2260/607 , Y02T50/675
Abstract: A gas turbine engine has a first particle separator stage including a surface for impacting air at outer periphery of an air flow passage, capturing impacted particles at the outer periphery, and routing captured particles towards a second particle separator stage. Air inward of the first particle separator stage passes towards a core of the engine. Cleaner air upstream of the second particle separator stage is utilized for an air function at a location other than the core engine. A particle discharge is disposed downstream of said second particle separator stage.
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公开(公告)号：US09944401B2
公开(公告)日：2018-04-17
申请号：US14646752
申请日：2013-03-15
Applicant: United Technologies Corporation
Inventor： Jesse M. Chandler , Gabriel L. Suciu
Abstract: An aircraft includes a propulsion supported within an aft portion of a fuselage A thrust reverser is mounted in the aft portion of the fuselage proximate the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser includes an upper blocker door movable about a first pivot axis to a deployed position and a lower blocker door movable about a second pivot axis not parallel to the first pivot axis.
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公开(公告)号：US09932905B2
公开(公告)日：2018-04-03
申请号：US14745606
申请日：2015-06-22
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Wesley K. Lord , Jesse M. Chandler
CPC classification number: F02C9/18 , F02C6/08 , F02C7/06 , F02C7/14 , F02K3/115 , F05D2230/31 , F05D2260/213 , Y02T50/675
Abstract: A gas turbine engine comprises a main fan that delivers air into a bypass duct and into a core engine. A heat exchanger is positioned within the bypass duct and receives a fluid to be cooled from a component associated with the gas turbine engine. A heat exchanger fan is positioned to draw air across the heat exchanger and a control for the heat exchanger fan. The control is programmed to stop operation of the fan during certain conditions, and to drive the heat exchanger fan under other conditions. A method of forming a heat exchanger is also disclosed.
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Patent Agency Ranking
公开(公告)号：US20180037331A1
公开(公告)日：2018-02-08
申请号：US15228359
申请日：2016-08-04
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: B64D27/14 , B64D33/04 , B64D2033/0226 , F01D5/02 , F01D9/02 , F02C3/10 , F02K3/062 , F04D29/321 , F04D29/325 , F05D2220/323 , F05D2240/60
Abstract: An aircraft engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan connected to the turbine via a shaft. The fan is positioned aft of the turbine, and the shaft is at least partially disposed in a fan inlet flowpath.
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公开(公告)号：US20180023474A1
公开(公告)日：2018-01-25
申请号：US15217108
申请日：2016-07-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Wesley K. Lord , Jesse M. Chandler , Steven H. Zysman
CPC classification number: F02C7/18 , B64D27/20 , F02C3/04 , F05D2220/323 , F05D2250/51 , F05D2260/232 , Y02T50/676
Abstract: A gas turbine engine has an inner housing surrounding a compressor, a combustor, and a turbine, with an inlet leading into the compressor, and a cooling sleeve defined radially outwardly of the inlet to the compressor for receiving cooling air radially outward of the compressor inlet. The cooling sleeve extends along a length of the engine, and radially outwardly of the inner housing, with the cooling air in the cooling sleeve being ejected at a downstream end to mix with products of combustion downstream of the turbine. An aircraft is also disclosed.
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公开(公告)号：US20170306853A1
公开(公告)日：2017-10-26
申请号：US15137640
申请日：2016-04-25
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Kurt J. Sobanski
CPC classification number: F02C7/32 , F02C3/04 , F02C7/25 , F02C9/00 , F02K3/06 , F05D2260/57 , F05D2260/96 , F05D2270/62
Abstract: An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component in communication with the mechanical component separated from the mechanical component by a firewall, the firewall comprising a first side and a second side, the second side having a lower operating temperature than the first side. A vibration isolation structure is located at the second side. The electronic module is connected thereto and includes at least one vibration isolator secured to the firewall to vibrationally isolate the electronic module from gas turbine engine vibrations.
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公开(公告)号：US20170306842A1
公开(公告)日：2017-10-26
申请号：US15443113
申请日：2017-02-27
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 , F02C3/067 , F02K3/077 , B64D27/18 , F02C7/36 , F02C9/18 , F02C3/06
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：US09790811B2
公开(公告)日：2017-10-17
申请号：US14652840
申请日：2013-06-07
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F01D25/162 , F02C7/12 , F02C7/20 , F02C7/32 , F05D2220/325 , F05D2260/60 , Y02T50/675
Abstract: A gas turbine engine has a turbine section, and a housing enclosing the turbine section, with a mount structure secured to the housing for mounting and including internal flow passages for delivering air to remote locations.
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