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公开(公告)号：US12060807B2
公开(公告)日：2024-08-13
申请号：US17287487
申请日：2019-10-10
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Gilles Alain Marie Charier , Caroline Marie Frantz , Loïc Paul Yves Guillotel , Vincent François Georges Millier
IPC: F01D5/02 , B64D27/33 , B64D35/022 , B64D35/023 , B64D35/024 , B64D35/026 , F01D15/10 , F02C7/268 , F02C7/32 , F02C7/36
CPC classification number: F01D5/02 , B64D27/33 , B64D35/022 , B64D35/023 , B64D35/024 , B64D35/026 , F01D15/10 , F02C7/268 , F02C7/32 , F02C7/36 , F05D2220/323 , F05D2220/76 , F05D2230/60 , F05D2240/20 , F05D2240/60
Abstract: An aircraft turbine engine includes a gas generator and a fan arranged upstream from the gas generator and configured to generate a main gas flow, one portion of which flows in a flow path of the gas generator to form a primary flow, and another portion of which flows in a flow path around the gas generator to form a secondary flow. The gas generator has a low-pressure body with a rotor driving the fan and a low-pressure compressor situated upstream from an intermediate housing. The turbine engine also includes an electric machine, mounted coaxially downstream from the fan and upstream from the intermediate housing. An intermediate shaft is driven by the rotor of the low-pressure body and drives rotors of the electric machine and of the low-pressure compressor.
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公开(公告)号：US20240243677A1
公开(公告)日：2024-07-18
申请号：US18154363
申请日：2023-01-13
Applicant: Hamilton Sundstrand Corporation
Inventor： Brennan Fox , Mustansir H. Kheraluwala
CPC classification number: H02P9/02 , B64D27/10 , F02C6/00 , F02C7/268 , F05D2220/323 , F05D2220/76 , F05D2260/85
Abstract: A variable frequency starter generator (VFSG) system includes a VFSG having a start mode and a generate mode, a permanent magnet generator (PMG) and a main generator section and an exciter section. The system also includes a controller electrically connected to the VFSG. The controller flow start mode three phase electrical power from aircraft power to the exciter of the VFSG in the start mode and flows single phase electrical power to the exciter of the VFSG in the generate mode. The controller includes: an input active rectifier that receives input AC power and converts it to DC power and provides it to across a positive rail and negative rail; an output inverter coupled to an output of the input active rectifier; and one or more line inductors connected along one or both of the positive rail and negative rail between the input active rectifier and the output inverter.
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公开(公告)号：US20240243638A1
公开(公告)日：2024-07-18
申请号：US18154351
申请日：2023-01-13
Applicant: Hamilton Sundstrand Corporation
Inventor： Brennan Fox , Mustansir H. Kheraluwala
CPC classification number: H02K7/1823 , F02C7/268 , H02K19/32 , H02M7/12 , H02P9/08 , F05D2220/768 , F05D2240/24 , H02P2101/30
Abstract: A variable frequency starter generator (VFSG) system includes a VFSG having a start mode and a generate mode, a permanent magnet generator (PMG) and a main generator section and an exciter section. The system also includes a controller electrically connected to the VFSG. The controller flow start mode three phase electrical power from aircraft power to the exciter of the VFSG in the start mode and flows single phase electrical power to the exciter of the VFSG in the generate mode. The controller includes: a passive rectifier that receives input AC power and converts it to DC power and provides it to across a positive rail and negative rail; an output inverter coupled to an output of the passive rectifier; and one or more line inductors connected along one or both of the positive rail and negative rail between the passive rectifier and the output inverter.
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公开(公告)号：US11846237B2
公开(公告)日：2023-12-19
申请号：US17195848
申请日：2021-03-09
Applicant: RTX 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 , F01D25/12 , F16H1/22 , H02K7/116 , H02K7/18 , F01D15/12 , F02C7/275
CPC classification number: F02C7/32 , F01D15/10 , F01D15/12 , F01D25/12 , F02C3/06 , F02C7/185 , F02C7/268 , F02C7/275 , F02C7/36 , F16H1/222 , H02K7/116 , H02K7/1823 , F05D2220/32 , F05D2260/4031 , F05D2260/85
Abstract: An exemplary gas turbine engine assembly includes a fan section including a fan, 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 towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox includes a set of gears. A compressor is driven by the first towershaft. A transmission couples a starter generator assembly to the 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 in response to rotation of the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft in response to rotation of the second towershaft.
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公开(公告)号：US11840968B2
公开(公告)日：2023-12-12
申请号：US17485982
申请日：2021-09-27
Applicant: RTX Corporation
Inventor： Matthew D. Teicholz , James W. Dunn , Christopher P. Kmetz , Louis A. Celiberti
IPC: F02C9/42 , F01D25/34 , F02C7/275 , F02C7/26 , F01D13/00 , B64D27/02 , B64D31/02 , F01D19/00 , F01D21/00 , F02C7/268
CPC classification number: F02C9/42 , B64D27/02 , B64D31/02 , F01D13/003 , F01D19/00 , F01D21/003 , F01D25/34 , F02C7/26 , F02C7/268 , F02C7/275 , F05D2220/323 , F05D2260/85 , F05D2270/13 , F05D2270/14
Abstract: An aspect includes a method for motoring control for multiple engines of an aircraft is provided. A controller can determine a motoring time of a first engine starting system to cool a first engine. The controller can compare the motoring time of the first engine starting system with a motoring time of one or more other engine starting systems of one or more other engines of the aircraft. The motoring time of the first engine starting system can be controlled relative to a tolerance of the motoring time of the one or more other engine starting systems by adjusting the motoring time of the first engine starting system relative to the one or more other engine starting systems in a motoring sequence based on comparing the motoring time of the first engine starting system with the motoring time of the one or more other engine starting systems.
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Patent Agency Ranking
公开(公告)号：US11668248B2
公开(公告)日：2023-06-06
申请号：US16895223
申请日：2020-06-08
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Dana Tomescu
CPC classification number: F02C9/00 , F01D19/02 , F01D21/00 , F01D25/34 , F02C7/268 , F05D2220/323 , F05D2260/85 , F05D2270/303 , F05D2270/313 , F05D2270/44 , F05D2270/708
Abstract: There is provided a rotor bow mitigation system and method for an aircraft engine. At least one value of at least one engine parameter prior to a shutdown of the engine is obtained, the at least one engine parameter comprising a first temperature internal to the engine. A second temperature external to the engine is measured and a motoring duration and a motoring interval for the engine are determined based on at least the first temperature and on the second temperature. Upon detecting a start indication for the engine, the engine is motored for the motoring duration and at the motoring interval.
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公开(公告)号：US20180187601A1
公开(公告)日：2018-07-05
申请号：US15842352
申请日：2017-12-14
Applicant: Airbus Operations, S.L.
CPC classification number: F02C7/06 , B64D41/00 , F01D25/10 , F01D25/20 , F02C7/14 , F02C7/22 , F02C7/268 , F05D2220/323 , F05D2220/76 , F05D2260/213 , F05D2260/85 , F05D2260/98 , F05D2270/303 , F28D7/0008 , Y02T50/671 , Y02T50/675
Abstract: An oil heating system in a turbine engine such as an aircraft turbojet or turboprop main engines, or in an aircraft auxiliary power unit (APU). The turbine oil heating system includes a turbine engine oil circuit for conducting lubricating oil to the turbine engine, an electric starter generator oil circuit for conducting cooling oil from the electric starter generator, and an oil-to-oil heat exchanger connected with the engine oil circuit and connectable with the electric starter generator oil circuit, for transferring heat from the starter generator oil to the engine oil as to warm-up the engine oil during turbine engine motoring prior to actual starting sequence. A low cost and highly integrated system is therefore provided for reducing drag torque of a turbine engine prior to the starting phase.
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8.发明申请公开(公告)号：US20180142619A1
公开(公告)日：2018-05-24
申请号：US15849640
申请日：2017-12-20
Applicant: Li SU
Inventor： Li SU
IPC: F02C3/067 , F01D5/02 , F04D19/00 , F04D29/32 , F01D5/18 , F01D5/14 , F04D29/54 , F04D29/056 , F02C7/268 , F02C7/36
CPC classification number: F02C3/067 , F01D1/20 , F01D1/26 , F01D5/02 , F01D5/141 , F01D5/18 , F02C7/268 , F02C7/36 , F04D19/005 , F04D25/024 , F04D29/056 , F04D29/321 , F04D29/325 , F04D29/541 , F05D2260/31 , Y02T50/671
Abstract: A multiple axle-sleeve driving bidirectional rotating wheel-shaped fan turbine and a bushing wheel-shaped fan compressor, including: a working component, a driving component, a structural and installed component and a starting component. A wheel-shaped fan of the turbine drives a corresponding wheel-shaped fan of compressor to rotate through a driving axle sleeve. A rotating direction of the wheel-shaped fan of the turbine is opposite to a rotating direction of a wheel-shaped fan adjacent to the wheel-fan and rotating speed of the plurality of wheel-shaped fan is different. Each of the auxiliary wheel-shape fans is respectively bushed on each of the wheel-shaped fans of the compressor. A turbojet assembled with this disclosure has a high functionality, a light weight, a quick heat dissipation, an excellent anti-surging and a low energy consumption.
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公开(公告)号：US09945246B2
公开(公告)日：2018-04-17
申请号：US15021071
申请日：2014-09-10
Applicant: TURBOMECA
IPC: F01D19/00 , G01M13/00 , F01D21/00 , F02C7/26 , F02C7/268 , F02C7/275 , F02C7/22 , F02C7/28 , F23R3/38
CPC classification number: F01D21/003 , F02C7/222 , F02C7/26 , F02C7/268 , F02C7/275 , F02C7/28 , F05D2220/30 , F05D2240/60 , F05D2260/80 , F05D2260/85 , F23R3/38
Abstract: The invention relates to a method (1000) for monitoring a degree of coking at the dynamic seals of a turbine engine comprising: a gas generator, comprising a rotary shaft and an injection wheel mounted on said shaft, an injection manifold, dynamic seals for ensuring a seal between the injection wheel and the injection manifold, and a starter, the method comprising the steps: measuring (1500), during a phase for initiating rotation of the shaft of the gas generator by the starter, a current flowing through the starter and a voltage on the terminals of the starter, determining (1600), from the measured current and voltage, a degree of coking at the dynamic seals. The invention also relates to a turbine engine comprising a system for monitoring a degree of coking.
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公开(公告)号：US09885288B2
公开(公告)日：2018-02-06
申请号：US15658473
申请日：2017-07-25
Applicant: Hamilton Sundstrand Corporation
Inventor： Jay M. Francisco
CPC classification number: F02C7/277 , F01D17/06 , F01D19/00 , F02C7/268 , F02C7/32 , F05B2270/32 , F05B2270/3201 , F05D2220/50 , H02P3/08
Abstract: An APU has a gas turbine engine and a starter generator to be selectively driven by the gas turbine engine. A sensor senses windmilling of components associated with the starter generator. A lock feature limits rotation within the starter generator when windmilling is sensed. A method of operation is also disclosed.
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