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公开(公告)号：US20190039740A1
公开(公告)日：2019-02-07
申请号：US16152929
申请日：2018-10-05
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu
Abstract: A disclosed gas turbine engine includes a fan section delivering air into a compressor section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use.
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公开(公告)号：US10156206B2
公开(公告)日：2018-12-18
申请号：US14512520
申请日：2014-10-13
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry
Abstract: A gas turbine engine that has a fan case radially surrounding a fan hub, and plural fan exit guide vanes rotatably connected between the fan hub and the fan case. The fan section also has a thrust reverser opening within the case, axially upstream of the guide vanes. The gas turbine engine also has a core case containing a core engine.
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公开(公告)号：US20180354637A1
公开(公告)日：2018-12-13
申请号：US15619893
申请日：2017-06-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Wesley K. Lord
Abstract: An exemplary boundary layer ingestion engine includes a gas generator, a turbine fluidly connected to the gas generator, and a fan mechanically linked to the turbine via at least one shaft. The linkage is configured such that rotation of the turbine is translated to the fan. The boundary layer ingestion engine further includes an exhaust duct fluidly connected to an outlet of the turbine. The exhaust duct is positioned radially inward of the fan.
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公开(公告)号：US10094393B2
公开(公告)日：2018-10-09
申请号：US15023289
申请日：2014-08-01
Applicant: United Technologies Corporation
Inventor： James D. Hill , Gabriel L. Suciu , Jesse M. Chandler
Abstract: A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades. The inlet frame connects to an inlet end of the compressor case. The outlet frame connects to an outlet end of the compressor case portion at an end opposite the compressor case inlet end. An axially fore mounting structure of the mounting structure connects to the inlet frame. An axially aft mounting structure of the mounting structure connects to the outlet frame. A bridging structure of the mounting structure is offset from the compressor case and connects the fore and aft mounting structures, thereby bridging engine loads across the inlet and outlet frames to reduce load induced distortion of the compressor case portion.
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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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Patent Agency Ranking
公开(公告)号：US20180283277A1
公开(公告)日：2018-10-04
申请号：US15943825
申请日：2018-04-03
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu
CPC classification number: F02C7/06 , F01D25/16 , F05D2240/50
Abstract: A geared turbofan gas turbine engine includes a fan section and a core section. The core section includes a compressor section, a combustor section and a turbine section. The fan section includes a gearbox and a fan. A low spool includes a low turbine within the turbine section and a forward connection to a gearbox for driving the fan. The low spool is supported for rotation about the axis at a forward most position by a forward roller bearing and at an aft position by a thrust bearing.
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公开(公告)号：US20180252162A1
公开(公告)日：2018-09-06
申请号：US15970516
申请日：2018-05-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nathan Snape , Gabriel L. Suciu , Brian D. Merry , James D. Hill , William K. Ackermann
IPC: F02C7/12
CPC classification number: F02C7/12 , F05D2260/213
Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.
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公开(公告)号：US20180230944A1
公开(公告)日：2018-08-16
申请号：US15943100
申请日：2018-04-02
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian Merry , Christopher M. Dye
Abstract: A turbine engine is disclosed that includes a fan case surrounding a fan rotatable about an axis. A core is supported relative to the fan case by support structure arranged downstream from the fan. The core includes a core housing having an inlet case arranged to receive airflow from the fan. A compressor case is arranged axially adjacent to the inlet case and surrounds a compressor stage having a rotor blade with a blade trailing edge. The support structure includes a support structure leading edge facing the fan and a support structure trailing edge on a side opposite the support structure leading edge. The support structure trailing edge is arranged axially forward of the blade trailing edge. In one example, a forward attachment extends from the support structure to the inlet case.
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公开(公告)号：US20180223668A1
公开(公告)日：2018-08-09
申请号：US15947119
申请日：2018-04-06
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve, JR. , James W. Norris
Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.
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公开(公告)号：US20180209343A1
公开(公告)日：2018-07-26
申请号：US15410971
申请日：2017-01-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , William K. Ackermann , Brian Merry , Neil Terwilliger
CPC classification number: F02C7/185 , F02C3/04 , F02K3/06 , F05D2260/213 , Y02T50/676
Abstract: An intercooled cooling system for a gas turbine engine includes a heat exchanger in fluid communication with a cooling airflow source directed through the heat exchanger and an auxiliary compressor fluidly coupled to the heat exchanger via a discharge duct to compress the cooling airflow exiting the heat exchanger. A compressor discharge pathway directs a first portion of the cooling airflow from the auxiliary compressor to a first cooling location of the gas turbine engine, and a bypass pathway is fluidly coupled to the discharge duct between the heat exchanger and the auxiliary compressor to direct a second portion of the cooling airflow to a second cooling location of the gas turbine without passing through the auxiliary compressor.
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