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公开(公告)号：US20180080373A1
公开(公告)日：2018-03-22
申请号：US15268713
申请日：2016-09-19
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Tania Bhatia Kashyap , Mark F. Zelesky , Arthur W. Utay , Gabriel L. Suciu , Thomas N. Slavens , Kevin L. Rugg , Brian Merry
CPC classification number: F02C3/107 , F02C3/145 , F02C7/04 , F05D2240/40 , F05D2250/30
Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.
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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：US20180030926A1
公开(公告)日：2018-02-01
申请号：US14615484
申请日：2015-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher A. Eckett , Gabriel L. Suciu
CPC classification number: F02K3/075 , B64D27/26 , B64D29/06 , B64D33/04 , B64D2027/266 , B64D2027/268 , F01D25/24 , F02C3/04 , F02K1/09 , F02K1/70 , F02K1/72 , F02K1/763 , F02K3/06 , F05D2240/14 , F05D2270/051 , Y02T50/671 , Y02T50/672
Abstract: A method of designing an engine according to an exemplary aspect of the present disclosure includes, among other things, designing an engine and a nacelle assembly together in an interactive process, the engine including a turbine section configured to drive a fan section and a compressor section. The step of designing the compressor section includes the step of designing a first compressor and a second compressor, with an overall pressure ratio being greater than or equal to about 35. The step of designing the nacelle assembly includes the step of designing the fan section to include a fan nacelle arranged at least partially about a fan, with the fan section having a fan pressure ratio of less than about 1.7. The step of designing the fan section includes configuring the fan section to deliver a portion of air into the compressor section, and a portion of air into a bypass duct, and with a bypass ratio equal to or greater than about 5.
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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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145.发明授权公开(公告)号：US09835052B2
公开(公告)日：2017-12-05
申请号：US15478671
申请日：2017-04-04
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
IPC: F02C7/36 , F01D25/16 , F04D29/32 , F04D25/04 , F04D19/02 , F01D5/06 , F01D9/04 , F02C3/107 , F01D15/12 , F02C3/04 , F02K3/06
CPC classification number: F01D25/164 , F01D5/06 , F01D9/041 , F01D15/12 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/028 , F04D25/045 , F04D29/056 , F04D29/325 , F04D29/668 , F05D2220/32 , F05D2240/60 , F05D2260/40311
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, and a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
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Patent Agency Ranking
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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148.发明申请公开(公告)号：US20170298767A1
公开(公告)日：2017-10-19
申请号：US15478706
申请日：2017-04-04
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
IPC: F01D25/16 , F01D9/04 , F04D19/02 , F01D5/06 , F04D29/32 , F04D27/00 , F04D25/04 , F04D25/02 , F02C3/04 , F02K3/06
CPC classification number: F01D25/164 , F01D5/06 , F01D9/041 , F01D15/12 , F01D25/162 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/028 , F04D25/045 , F04D27/009 , F04D29/056 , F04D29/325 , F04D29/668 , F05D2220/32 , F05D2240/60 , F05D2260/40311
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
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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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公开(公告)号：US09790792B2
公开(公告)日：2017-10-17
申请号：US14302884
申请日：2014-06-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Stephen P. Muron , Christopher M. Dye , Ioannis Alvanos , Brian D. Merry
CPC classification number: F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
Abstract: A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.
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