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公开(公告)号：US09845726B2
公开(公告)日：2017-12-19
申请号：US14568167
申请日：2014-12-12
Applicant: United Technologies Corporation
CPC classification number: F02C3/06 , F02C3/04 , F02C7/36 , F02K3/02 , F02K3/04 , F02K3/06 , F02K3/072 , F05D2220/3215
Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：US09828914B2
公开(公告)日：2017-11-28
申请号：US14685392
申请日：2015-04-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
CPC classification number: F02C7/047 , B64C11/14 , F01D25/02 , F01D25/12 , F01D25/125 , F02C7/06 , F05D2260/213 , Y02T50/676
Abstract: A thermal management system and method of circulating air in a gas turbine engine are disclosed. The thermal management system includes a nose cone having an aperture communicating air to an interior space of the nose cone and a fan blade coupled to the nose cone and having a blade passage, wherein the nose cone rotates with the fan blade to circulate air from the aperture to the blade passage.
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公开(公告)号：US20170306852A1
公开(公告)日：2017-10-26
申请号：US15137614
申请日：2016-04-25
Applicant: United Technologies Corporation
Inventor： Paul Attridge , Gabriel L. Suciu , Kurt J. Sobanski , Jesse M. Chandler
CPC classification number: F02C7/32 , B64C27/625 , B64C27/64 , B64C27/68 , B64C33/00 , F02C3/04 , F02C7/20 , F02C7/25 , F02C7/36 , F02K3/06 , F05D2260/57 , F05D2270/62 , H02K7/003 , H02K11/20
Abstract: An electromechanical system for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine, and an electrical motor located at a second side of the firewall and configured to drive the mechanical component. The electrical motor mechanically connected to the mechanical component through a firewall opening in the firewall, the first side having a higher operating temperature than the second side. An electrical connection extends between the mechanical component and the electrical motor via the same firewall opening.
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公开(公告)号：US20170306847A1
公开(公告)日：2017-10-26
申请号：US15138269
申请日：2016-04-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler
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 first 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. A second tap taps air from the compressor section, passes the air across a cabin air pump, and delivers air from the cabin air pump for use on an aircraft receiving the gas turbine engine. The cooling compressor including a rotor, and the cabin air pump including a rotor, and a drive driven with the turbine section in turn drives both the cooling compressor rotor and the cabin air supply rotor. A combined intercooling system and cabin air supply system is also disclosed.
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公开(公告)号：US20170298757A1
公开(公告)日：2017-10-19
申请号：US15638954
申请日：2017-06-30
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 according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. A fan shaft support supports the fan shaft and a gear system is connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. At least one of said gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
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Patent Agency Ranking
公开(公告)号：US20170283073A1
公开(公告)日：2017-10-05
申请号：US15089713
申请日：2016-04-04
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , William K. Ackermann
CPC classification number: B64D13/06 , B64D2013/0618 , F02C3/04 , F02C6/08 , F02C7/18 , F02C9/18 , F02K3/06 , F05D2260/608
Abstract: An environmental control system for an aircraft includes a higher pressure tap to be associated with a higher compression location in a main compressor section associated with an aircraft engine, and a lower pressure tap to be associated with a lower pressure location in the main compressor section associated with the aircraft engine. The lower pressure location being at a lower pressure than the higher 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 turbine outlet receives airflow exhausted from the turbine section. A compressor outlet receives airflow exhausted from the compressor section. A combined outlet receives airflow from the turbine outlet and the compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft. A diverter valve controls airflow from the turbine outlet into the combined outlet for controlling a temperature of airflow in the combined outlet. A gas turbine engine is also disclosed.
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公开(公告)号：US20170276012A1
公开(公告)日：2017-09-28
申请号：US15079400
申请日：2016-03-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jesse M. Chandler , Gabriel L. Suciu , Joseph Stack
CPC classification number: F01D17/162 , F01D9/04 , F01D9/041 , F01D9/042 , F01D17/105 , F01D17/12 , F01D17/14 , F01D17/16 , F01D25/34 , F02K3/02 , F05D2220/323 , F05D2260/40 , 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：US20170276009A1
公开(公告)日：2017-09-28
申请号：US15606386
申请日：2017-05-26
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 according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support said that supports fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear lateral stiffness and a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral stiffness and the ring gear transverse stiffness is less than 12% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.
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公开(公告)号：US20170254268A1
公开(公告)日：2017-09-07
申请号：US15058229
申请日：2016-03-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Wesley K. Lord , Nathan Snape , Gabriel L. Suciu
IPC: F02C7/18
Abstract: A gas turbine engine component includes a heat exchange structure having an upstream end and a downstream end. A diffusing duct is associated with the upstream end. A throttle member controls air flow through the heat exchange structure, wherein the throttle member: (a) has a non-circular cross section; and (b) is mounted to the downstream end of the heat exchange structure or is mounted between the upstream end and the diffusing duct.
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公开(公告)号：US20170218850A1
公开(公告)日：2017-08-03
申请号：US15485563
申请日：2017-04-12
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 defined 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 between 0.5 and 1.5.
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