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31.发明申请公开(公告)号：US20180202368A1
公开(公告)日：2018-07-19
申请号：US15410113
申请日：2017-01-19
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Hung Duong , Jonathan F. Zimmitti , William G. Sheridan , Michael E. McCune , Brian Merry
IPC: F02C7/32 , F02C3/06 , F02C7/18 , F02C7/36 , F02C7/268 , F01D15/10 , F01D15/12 , F01D25/12 , F16H1/22 , H02K7/116 , H02K7/18
CPC classification number: F02C7/32 , F01D15/10 , F01D15/12 , F01D25/12 , F02C3/06 , F02C7/185 , F02C7/268 , F02C7/275 , F02C7/36 , F05D2220/32 , F05D2260/4031 , F05D2260/85 , F16H1/222 , H02K7/116 , H02K7/1823
Abstract: An exemplary gas turbine engine assembly includes a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second turbines are mounted for rotation about a common rotational axis within an engine static structure. The first and second turbine shafts are coaxial with one another. First and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox has a set of gears. A compressor is driven by the first towershaft. The engine assembly further includes a starter generator assembly, and a transmission coupling the starter generator assembly to the first set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft.
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公开(公告)号：US20180202367A1
公开(公告)日：2018-07-19
申请号：US15409974
申请日：2017-01-19
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Hung Duong , Jonathan F. Zimmitti , William G. Sheridan , Michael E. McCune , Brian Merry
IPC: F02C7/32 , F02C7/277 , F02C7/22 , F01D15/10 , F01D15/08 , F01D15/12 , F01D5/06 , F01D25/20 , F01D25/16
CPC classification number: F02C7/32 , F01D5/06 , F01D15/08 , F01D15/10 , F01D15/12 , F01D25/16 , F01D25/20 , F02C7/22 , F02C7/277 , F02C7/36 , F05D2220/32 , F05D2220/50 , F05D2240/60 , F05D2260/4031
Abstract: A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, the accessory drive gearbox including a first gear train and a second gear train, the first towershaft extending into a housing and coupled to the first gear train, the second towershaft extending into the housing and coupled to the second gear train, a hydraulic pump, a transmission coupling the hydraulic pump to the first gear train, the transmission transitionable between a first mode where the hydraulic pump is driven at a first speed relative to the first towershaft, a second mode where the hydraulic pump is driven at a different, second speed relative to the first towershaft, and a third mode where the hydraulic pump is driven at a different, third speed relative to the first towershaft.
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公开(公告)号：US20180106194A1
公开(公告)日：2018-04-19
申请号：US15784629
申请日：2017-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brian Merry , Gabriel L. Suciu , James W. Norris
CPC classification number: F02C3/073 , F02K1/04 , F02K3/068 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y10T29/49346
Abstract: A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
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公开(公告)号：US20160032937A1
公开(公告)日：2016-02-04
申请号：US14793503
申请日：2015-07-07
Applicant: United Technologies Corporation
Inventor： James Hill , Brian Merry , Gabriel Suciu
CPC classification number: F04D29/083 , F01D11/005 , F01D11/006 , F04D17/08 , F04D17/122 , F04D29/284 , F04D29/286 , F05B2230/236
Abstract: A gas turbine engine includes an axial compressor which includes a rotor assembly including a first rotor segment with a first inner rim, a first sealing surface, and a first aft engagement feature, and a second rotor segment positioned aft of the first rotor segment and having a second inner rim, a second sealing surface, and a second inner rim with a second fore engagement feature that is complementary to the first aft engagement feature. The first and second sealing surfaces are complementary to each other, and are bonded together via a transient liquid phase diffusion process. The first and second sealing surfaces are disposed on the outer rim. The first aft engagement member may be a notch that is complementary to the second fore engagement feature, which may be a shelf.
Abstract translation: 一种燃气涡轮发动机包括轴向压缩机，其包括转子组件，该转子组件包括具有第一内缘的第一转子段，第一密封表面和第一后部接合特征，以及定位在第一转子段后面的第二转子段， 第二内边缘，第二密封表面和具有与第一后部接合特征互补的第二前部接合特征的第二内部边缘。 第一和第二密封表面彼此互补，并通过瞬态液相扩散工艺结合在一起。 第一和第二密封面设置在外缘上。 第一尾部接合构件可以是与第二前部接合特征互补的凹口，其可以是搁架。
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公开(公告)号：US11130580B2
公开(公告)日：2021-09-28
申请号：US15809244
申请日：2017-11-10
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian Merry , Stephen H. Taylor , Charles E. Lents
IPC: F02C6/08 , B64D13/08 , F02C9/18 , F02K3/115 , B64D27/10 , F01D15/10 , F02C3/04 , F02K3/06 , H02K7/18 , F02C7/18 , F02K3/04 , B64D13/06
Abstract: An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.
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Patent Agency Ranking
公开(公告)号：US10794214B2
公开(公告)日：2020-10-06
申请号：US15589009
申请日：2017-05-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Mark F. Zelesky , Ioannis Alvanos , Brian Merry
Abstract: A clearance control system for a gas turbine engine comprises at least one case support associated with an engine case defining an engine center axis. A clearance control ring is positioned adjacent the at least one case support to form an internal cavity between the engine case and the clearance control ring. The clearance control ring includes a first mount feature. An outer air seal has a second mount feature cooperating with the first mount feature such that the clearance control ring can move independently of the engine case in response to changes in temperature. An injection source inject flow into the internal cavity to control a temperature of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and an engine component. A gas turbine engine and a method of controlling tip clearance in a gas turbine engine are also disclosed.
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公开(公告)号：US10731560B2
公开(公告)日：2020-08-04
申请号：US15907942
申请日：2018-02-28
Applicant: United Technologies Corporation
Inventor： Nathan Snape , Gabriel L. Suciu , Brian Merry , Jesse M. Chandler , Frederick M. Schwarz
Abstract: A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A first tap is connected to the compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap and configured to deliver air to an aircraft fuselage. A cooling compressor is connected downstream of the heat exchanger. A high pressure feed is configured to deliver air at a second pressure which is higher than the first pressure. The cooling compressor is configured to deliver air to at least one of the plurality of rotating components. A valve assembly that can select whether air from the first tap or air from the high pressure feed is delivered to the aircraft pneumatic system.
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公开(公告)号：US10605173B2
公开(公告)日：2020-03-31
申请号：US16456087
申请日：2019-06-28
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Hung Duong , Jonathan F. Zimmitti , William G. Sheridan , Michael E. McCune , Brian Merry
Abstract: A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.
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公开(公告)号：US10590853B2
公开(公告)日：2020-03-17
申请号：US15409974
申请日：2017-01-19
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Hung Duong , Jonathan F. Zimmitti , William G. Sheridan , Michael E. McCune , Brian Merry
IPC: F02C7/32 , F02C7/277 , F02C7/22 , F01D15/10 , F01D15/08 , F01D15/12 , F01D5/06 , F01D25/20 , F01D25/16 , F02C7/36 , F01D5/02 , F02C7/06
Abstract: A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, a hydraulic pump, and a transmission. The transmission is transitionable between a first mode where the hydraulic pump is driven at a first speed relative to a first towershaft, a second mode where the hydraulic pump is driven at a different, second speed relative to the first towershaft, and a third mode where the hydraulic pump is driven at a different, third speed relative to the first towershaft.
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公开(公告)号：US20190316526A1
公开(公告)日：2019-10-17
申请号：US16456087
申请日：2019-06-28
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Hung Duong , Jonathan F. Zimmitti , William G. Sheridan , Michael E. McCune , Brian Merry
Abstract: A gas turbine engine comprises a low speed spool and a high speed spool, with each of the spools including a turbine to drive a respective one of the spools. The high speed spool rotates at a higher speed than the low speed spool. A high speed power takeoff is driven to rotate by the high speed spool, and a low speed power takeoff is driven to rotate by the low speed spool. The high speed power takeoff drives a starter generator and a permanent magnet alternator. The low speed power takeoff drives a variable frequency generator.
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