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公开(公告)号：US20170276016A1
公开(公告)日：2017-09-28
申请号：US15079469
申请日：2016-03-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F01D17/162 , F05D2220/32 , F05D2240/12 , F05D2250/14 , F05D2260/53 , F05D2260/532 , F05D2260/57 , F16H19/001 , F16H37/12 , F16H49/001 , F16H55/17 , Y02T50/671
Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.
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公开(公告)号：US20170276014A1
公开(公告)日：2017-09-28
申请号：US15079432
申请日：2016-03-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jesse M. Chandler , Gabriel L. Suciu
CPC classification number: F01D17/162 , F01D7/00 , F01D9/04 , F01D9/042 , F01D17/12 , F01D17/14 , F01D17/165 , F01D25/34 , F04D29/323 , F04D29/563 , F05D2220/32 , F05D2240/128 , F16H49/001 , Y02T50/671 , Y02T50/673
Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.
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公开(公告)号：US20170276013A1
公开(公告)日：2017-09-28
申请号：US15079417
申请日：2016-03-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jonathan F. Zimmitti , Jesse M. Chandler
CPC classification number: F01D17/162 , F05D2220/32 , F05D2240/12 , F05D2260/57 , F16H19/001 , F16H49/001 , Y02T50/671 , Y02T50/673
Abstract: An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.
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公开(公告)号：US09771863B2
公开(公告)日：2017-09-26
申请号：US14600304
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Alan H. Epstein , Wesley K. Lord , Jesse M. Chandler , Stephen G. Pixton
Abstract: An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed.
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公开(公告)号：US20170234267A1
公开(公告)日：2017-08-17
申请号：US15586386
申请日：2017-05-04
Applicant: United Technologies Corporation
Inventor： Jesse M. Chandler , Gabriel L. Suciu
CPC classification number: F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
Abstract: A pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a first sliding rail. A second tandem pivot door subassembly is included comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a second sliding rail.
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Patent Agency Ranking
公开(公告)号：US20170218849A1
公开(公告)日：2017-08-03
申请号：US15484441
申请日：2017-04-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.
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公开(公告)号：US09714610B2
公开(公告)日：2017-07-25
申请号：US13645067
申请日：2012-10-04
Applicant: United Technologies Corporation
Inventor： Nathan Snape , Gabriel L. Suciu , Simon Pickford , Allan R. Penda
CPC classification number: F02C6/08 , F02C7/14 , F05D2260/213 , Y02T50/672 , Y02T50/675
Abstract: An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.
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公开(公告)号：US20170175633A1
公开(公告)日：2017-06-22
申请号：US15445521
申请日：2017-02-28
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Brian Merry
CPC classification number: F02C7/20 , B64D27/10 , B64D27/26 , B64D2027/262 , B64D2027/266 , F05D2220/323 , F05D2230/60 , F05D2240/90 , Y02T50/44 , Y10T29/49947
Abstract: A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.
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公开(公告)号：US20170167388A1
公开(公告)日：2017-06-15
申请号：US14967446
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Michael G. McCaffrey
CPC classification number: F02C9/18 , F01D17/105 , F01D25/12 , F02C7/143 , F02C7/185 , F02C7/32 , F02C7/36 , F04D29/284 , F05D2220/32 , F05D2220/3212 , F05D2260/211 , F05D2260/213 , F05D2260/4031 , F05D2260/606 , F05D2270/112 , F05D2270/335 , Y02T50/676
Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor, and at least one more upstream compressor. A turbine section has a high pressure turbine. A tap line taps air from at least one of the more upstream compressors 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. A bypass valve is positioned downstream of the main compressor section, and upstream of the heat exchanger. The bypass valve selectively delivers air directly to the cooling compressor without passing through the heat exchanger under certain conditions. An intercooling system is also disclosed.
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公开(公告)号：US20170159572A1
公开(公告)日：2017-06-08
申请号：US15437104
申请日：2017-02-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael E. McCune , Jason Husband , Frederick M. Schwarz , Daniel Bernard Kupratis , Gabriel L. Suciu , William K. Ackermann
CPC classification number: F01D15/12 , F01D5/06 , F01D9/041 , F02C3/107 , F02C7/20 , F02C7/36 , F02K3/06 , F04D19/002 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2240/60 , F05D2260/4031 , F05D2260/40311 , F05D2300/501 , Y02T50/671
Abstract: A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with some flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a second speed, which is faster than said first speed. A performance quantity can be defined for both turbine sections as the products of the respective areas and respective speeds squared. A performance quantity ratio of the performance quantity for the fan drive turbine to the performance quantity for the second turbine section is relatively high.
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