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公开(公告)号：US10823056B2
公开(公告)日：2020-11-03
申请号：US15371589
申请日：2016-12-07
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
IPC: F02C6/08 , F02K3/06 , F02C7/36 , F02C3/20 , B64D33/02 , F02C3/10 , B64D27/20 , F02K3/062 , B64C1/16 , B64C21/00
Abstract: A boundary layer ingestion engine includes a gas generator and a turbine fluidly connected to the gas generator. A fan is mechanically linked to the turbine via a shaft such that rotation of the turbine is translated to the fan. A boundary layer ingestion inlet is aligned with an expected boundary layer, such that the boundary layer ingestion inlet is configured to ingest fluid from a boundary layer during operation of the boundary layer ingestion engine.
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公开(公告)号：US10526915B2
公开(公告)日：2020-01-07
申请号：US15062442
申请日：2016-03-07
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Brian D. Merry
IPC: F01D25/08 , F02C7/25 , F02C7/36 , F02C7/32 , F01D25/20 , F02C7/22 , F04D19/02 , F04D27/00 , F04D29/56
Abstract: A gas turbine engine comprises an engine having a compressor section, and a turbine section. A firewall and accessory pumps are mounted on a downstream side of the firewall. The accessory pumps are driven by electric motors mounted on the firewall on an upstream side of the firewall.
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公开(公告)号：US20200003228A1
公开(公告)日：2020-01-02
申请号：US16507553
申请日：2019-07-10
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine includes a harmonic drive driven by an actuator, a drive shaft driven by the harmonic drive, the drive shaft with a first drive gear and a second drive gear. A first variable vane stage with a first actuator gear to direct drive one of a multiple of variable vanes, the first actuator gear meshed with the first drive gear; and a second variable vane stage with a second actuator gear to direct drive one of a multiple of variable vanes, the second actuator gear meshed with the second drive gear.
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公开(公告)号：US20190323789A1
公开(公告)日：2019-10-24
申请号：US16502518
申请日：2019-07-03
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry
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 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. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：US10309310B2
公开(公告)日：2019-06-04
申请号：US14758277
申请日：2013-05-10
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Wesley K. Lord
Abstract: In a featured embodiment, a gas turbine engine has a first compressor rotor driven by a first turbine rotor, and a second compressor rotor driven by a second turbine rotor. The second compressor rotor is upstream of the first compressor rotor and the first turbine rotor is upstream of the second turbine rotor. An air mixing system taps air from a location upstream of the first compressor rotor for delivery to an environmental control system. The air mixing system receives air from a first air source and a second air source. The first air source includes air at a first pressure upstream of the first compressor rotor. The second air source includes air at a lower second pressure. At least one valve controls a mixture of air from the first and second sources to achieve a predetermined pressure for the environmental control system.
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Patent Agency Ranking
公开(公告)号：US20190162118A1
公开(公告)日：2019-05-30
申请号：US16264837
申请日：2019-02-01
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02C7/18 , B64D2013/0603 , F01D25/12 , F02C6/08 , F02C9/18 , F02K3/06 , F02K3/062 , F05D2220/324 , F05D2220/327 , F05D2250/51 , Y02T50/675
Abstract: A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.
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公开(公告)号：US10156188B2
公开(公告)日：2018-12-18
申请号：US15137509
申请日：2016-04-25
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Kurt J. Sobanski , Jesse M. Chandler
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 connected to the mechanical component by a module cable. The electronic module is inserted through a module opening in the firewall from the first side to a second side, the second side having a lower operating temperature than the first side. A cover plate is installed over the module opening after the electronic module is inserted therethrough.
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公开(公告)号：US20180258859A1
公开(公告)日：2018-09-13
申请号：US15978455
申请日：2018-05-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry , Wesley K. Lord
CPC classification number: F02C7/185 , F01D25/12 , F02C3/13 , F02C6/08 , F02C7/143 , F02C7/32 , F02K3/115 , F05D2210/44 , F05D2220/3212 , F05D2220/3218 , F05D2260/211 , F05D2260/213 , F05D2260/606 , Y02T50/675 , Y02T50/676
Abstract: A gas turbine engine includes a main compressor. A tap is fluidly connected downstream of the main compressor. A heat exchanger is fluidly connected downstream of the tap. An auxiliary compressor unit is fluidly connected downstream of the heat exchanger. The auxiliary compressor unit is configured to compress air cooled by the heat exchanger with an overall auxiliary compressor unit pressure ratio between 1.1 and 6.0. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：US20180237147A1
公开(公告)日：2018-08-23
申请号：US15439988
申请日：2017-02-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: B64D27/26 , B64D27/20 , B64D35/04 , B64D2027/268
Abstract: A propulsor and mount arrangement comprises a propulsor rotor and a fan casing surrounding the propulsor rotor. The fan casing receives two side mounts and a thrust link pivotally attached to the fan casing at a location that will be within 10° of a vertically lowermost location when the propulsor is mounted on an aircraft, and the side mounts being at circumferentially opposed positions, and within a lower 270° when the propulsor is mounted on an aircraft. At least a portion of both the side mounts, and a pivot point connect the thrust link to the fan casing in a common plane defined perpendicular to a rotational axis of the propulsor rotor. An aircraft is also disclosed.
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公开(公告)号：US10001063B2
公开(公告)日：2018-06-19
申请号：US14440698
申请日：2013-03-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02C7/20 , B64D27/20 , B64D33/02 , B64D2033/0286 , F05D2250/314
Abstract: A propulsion system for an aircraft includes first and second turbine engines mounted within a fuselage of the aircraft. The first turbine engine includes a first engine core that drives a first propulsor disposed about a first propulsor axis. The second turbine engine includes a second engine core and a second propulsor disposed about a second propulsor axis parallel to the first propulsor axis. The first engine core and the second engine core are mounted at an angle relative to corresponding ones of the first and second propulsor axes.
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