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公开(公告)号：US10480419B2
公开(公告)日：2019-11-19
申请号：US14745567
申请日：2015-06-22
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 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, passing the tapped air through a first heat exchanger and then to a cooling compressor. A second tap taps air from a location closer to the downstream most end than the location of the first tap, and the first and second taps mix together and are delivered into the high pressure turbine. The cooling compressor is positioned downstream of the first heat exchanger, and upstream of a location where air from the first and second taps mix together.
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公开(公告)号：US10287991B2
公开(公告)日：2019-05-14
申请号：US14600101
申请日：2015-01-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine comprises a gas generator rotating along a first axis of rotation, with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine rotates along a second axis of rotation, downstream of at least one gas generator turbine rotor. The fan drive turbine drives a pair of shaft portions extending in opposed directions beyond the axis of rotation of the gas generator.
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公开(公告)号：US10267263B2
公开(公告)日：2019-04-23
申请号：US15230590
申请日：2016-08-08
Applicant: United Technologies Corporation
Inventor： Wesley K. Lord , Jesse M. Chandler , Gabriel L. Suciu
Abstract: A gas turbine engine includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A propulsor section aft of the core engine is driven by the turbine section. An exhaust duct routing exhaust gases around the propulsor section. The exhaust duct includes an inlet forward of the propulsor section, an outlet aft of the turbine section and a passageway between the inlet and the outlet. An aircraft and exhaust duct are also disclosed.
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公开(公告)号：US10267236B2
公开(公告)日：2019-04-23
申请号：US15137640
申请日：2016-04-25
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Kurt J. Sobanski
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：US10215096B2
公开(公告)日：2019-02-26
申请号：US14932066
申请日：2015-11-04
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
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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Patent Agency Ranking
公开(公告)号：US10161358B2
公开(公告)日：2018-12-25
申请号：US14773958
申请日：2014-03-13
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines.
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公开(公告)号：US10112696B2
公开(公告)日：2018-10-30
申请号：US14440887
申请日：2013-03-15
Applicant: United Technologies Corporation
Inventor： Jesse M. Chandler , Gabriel L. Suciu
Abstract: An aircraft assembly is disclosed and includes a fuselage including a turbine engine mounted within the aft fuselage. A burst zone is defined about the turbine engine and a tail is disposed at least partially with the burst zone. The tail includes primary control surfaces and sacrificial control surfaces. The sacrificial control surfaces can break away in a defined manner to maintain integrity of the primary control surfaces outside of the burst zone.
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公开(公告)号：US20180258860A1
公开(公告)日：2018-09-13
申请号：US15978517
申请日：2018-05-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Brian D. Merry , Nathan Snape
CPC classification number: F02C7/185 , F02C3/04 , F02C7/32 , F02C9/18 , F05D2220/323 , F05D2240/90 , F05D2260/213 , F05D2260/4031
Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A tap connects to the compressor section. A heat exchanger connects downstream of the tap. A cooling compressor connects downstream of the heat exchanger, and the cooling compressor connects to deliver air to at least one of the rotating components. A core housing has an outer peripheral surface and a fan housing defines an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is disposed within the at least one bifurcation duct.
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公开(公告)号：US20180163664A1
公开(公告)日：2018-06-14
申请号：US15373101
申请日：2016-12-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
IPC: F02K3/062
CPC classification number: F02K3/062 , B64D27/10 , B64D35/04 , B64D35/08 , F01D13/003 , F02C3/107 , F05D2250/312
Abstract: A propulsion system for an aircraft has at least two fans, each fan having a fan drive shaft. A turboshaft gas turbine engine drives each of the at least two fans, and drive an output shaft which drives a gear to, in turn, engage for driving 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 ng the fan drive shaft, and the first intermediate shafts extending over a distance that is greater in an axial dimension defined between the turboshaft gas turbine engine and the fan than in a width dimension defined between the at least two fans. The first intermediate shafts are concentric.
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公开(公告)号：US20180066587A1
公开(公告)日：2018-03-08
申请号：US15807911
申请日：2017-11-09
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry , Wesley K. Lord
Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, 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 ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.
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