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公开(公告)号：US09874150B2
公开(公告)日：2018-01-23
申请号：US14222919
申请日：2014-03-24
CPC分类号： F02C7/36 , F02C3/107 , F02C7/32 , F02K3/06 , F05D2230/60 , F05D2260/40311 , F16H1/28 , F16H57/023 , F16H57/0423 , F16H57/0456 , F16H57/0479 , F16H57/0486 , F16H57/082 , Y02T50/671 , Y10T29/49464
摘要： A method of assembling an epicyclic gear train comprises the steps of providing a unitary carrier having a central axis that includes spaced apart walls and circumferentially spaced connecting structure defining spaced apart apertures provided at an outer circumference of the carrier. Gear pockets are provided between the walls and extend to the apertures. A central opening is in at least one of the walls. A plurality of intermediate gears are inserted through the central opening and move the intermediate gears radially outwardly into the gear pockets to extend into the apertures. A sun gear is inserted through the central opening. The plurality of intermediate gears is moved radially inwardly to engage the sun gear.
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公开(公告)号：US20180010522A1
公开(公告)日：2018-01-11
申请号：US15201837
申请日：2016-07-05
发明人： Benjamin T. Harder , Matthew Allen Slayter , Brian McMasters , James Vandung Nguyen , Dwayne Leon Wilson , Paul F. Fox , Richard Alan Davis , Richard R. Hergert , Jeffrey Todd Roberts , Jeff A. Brown , Daniel Richard Walker
CPC分类号： F02C7/275 , F01D21/12 , F01D25/34 , F02C7/277 , F02C7/32 , F02C7/36 , F05D2220/32 , F05D2220/323 , F05D2230/60 , F05D2260/40311 , F05D2260/85 , F16H1/46
摘要： According to an aspect, a system for a gas turbine engine includes a reduction gear train operable to drive rotation of a starter gear train that interfaces to an accessory gearbox of the gas turbine engine. The reduction gear train includes a starter interface gear that engages the starter gear train, a core-turning clutch operably connected to the starter interface gear, and a plurality of stacked planetary gear systems operably connected to the core-turning clutch and a core-turning input. The system also includes a mounting pad including an interface to couple a core-turning motor to the core-turning input of the reduction gear train.
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公开(公告)号：US20170363098A1
公开(公告)日：2017-12-21
申请号：US15186729
申请日：2016-06-20
CPC分类号： F04D27/009 , F01D5/02 , F01D15/08 , F01D15/12 , F01D17/145 , F02C6/08 , F02C7/32 , F04D25/02 , F04D27/004 , F04D27/023 , F04D29/321 , F05D2220/32 , F05D2260/4031 , F05D2260/40311
摘要： A gas turbine engine includes a main engine compressor section. A booster compressor changing a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system. The booster compressor operates at airflow conditions greater than a demand by the pneumatic system. A speed change system driving the booster compressor at speeds corresponding to a demand of the pneumatic system. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.
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公开(公告)号：US20170356345A1
公开(公告)日：2017-12-14
申请号：US15180728
申请日：2016-06-13
CPC分类号： F02C7/277 , F02C7/268 , F02C7/275 , F02C7/32 , F02C7/36 , F05D2220/32 , F05D2260/85 , F16D9/08
摘要： A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes a an output shaft, drive shaft, and a retention mechanism selectively coupling the output shaft to the drive shaft. In a backdrive event, the decoupler decouples the output shaft from the drive shaft.
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85.发明授权公开(公告)号：US09841038B2
公开(公告)日：2017-12-12
申请号：US13911346
申请日：2013-06-06
申请人： MICROTURBO SA
IPC分类号： F01D17/00 , F01D17/06 , F01D17/08 , F01D17/10 , F02C6/08 , F02C7/32 , F02C9/18 , F02C9/28 , F04D27/02 , F15B15/00 , F01D17/16 , F02C6/06 , F02C9/26 , B64D41/00
CPC分类号： F15B15/00 , B64D41/00 , F01D17/00 , F01D17/06 , F01D17/08 , F01D17/105 , F01D17/16 , F02C6/06 , F02C6/08 , F02C7/32 , F02C9/18 , F02C9/26 , F02C9/28 , F04D27/02 , F04D27/0207 , F04D27/0215 , F04D27/0223 , F04D27/023 , F05B2220/60 , F05D2220/50 , F05D2270/3015 , F05D2270/304
摘要： A system for supplying compressed air to a pneumatic network includes a load compressor, an air supply and a power shaft driving the load compressor. The system also includes in an air outlet of such load compressor, a connecting channel connected, on the one side, with a channel connected with the pneumatic network and, on the other side, with an air discharge conduct towards an exhaust nozzle. Air flow rate bleed valves are controlled by a processing unit via servo-loops as a function of the pressure sensors and the speed sensor.
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公开(公告)号：US20170350540A1
公开(公告)日：2017-12-07
申请号：US15174311
申请日：2016-06-06
IPC分类号： F16L9/18
CPC分类号： F16L9/18 , F01D25/00 , F01D25/18 , F02C7/00 , F02C7/222 , F02C7/32 , F05D2240/40 , F16L7/00 , F16L39/005 , F16L2201/30
摘要： Aspects of the disclosure are directed to a tube assembly comprising: a first tube having a radial exterior surface, a second tube composed of a plurality of segments, the first tube co-axially nested within the second tube, at least a first spacer coupled to the first tube, and a second spacer coupled to the at least a first spacer, where a first segment of the plurality of segments is coupled to a first axial end of the second spacer, and a second segment of the plurality of segments is coupled to a second axial end of the second spacer.
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公开(公告)号：US20170350317A1
公开(公告)日：2017-12-07
申请号：US15612264
申请日：2017-06-02
申请人： DIEHL AEROSPACE GMBH
发明人： Steffen POGGEL , Sven SCHMIDT
CPC分类号： F02C6/08 , F02C6/203 , F02C7/22 , F02C7/32 , F05D2220/32 , F05D2260/601
摘要： The invention relates to an arrangement (1, 15), comprising a turbomachine (2, 16) with a compressor (3) having an outlet (7), and with a bleed air line (9), through which a leakage flow can flow and which is connected via a controllable valve (8) to the outlet (7) of the compressor (3), for supplying the leakage flow to a unit, characterized in that the unit is designed as a fan (17), jet pump (10) or pump which can be driven by the leakage flow. The invention also relates to a method for operating the arrangement (1, 15).
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88.发明授权公开(公告)号：US09828109B2
公开(公告)日：2017-11-28
申请号：US14338711
申请日：2014-07-23
发明人： Lazar Mitrovic , Richard Ullyott
CPC分类号： B64D41/00 , B64C11/02 , B64C11/44 , B64D15/12 , B64D15/14 , B64D27/10 , F02C7/32 , F05D2260/40311 , F16H3/666
摘要： Apparatus and methods for generating electrical power for powering a device associated with a bladed rotor driven by a gas turbine engine of an aircraft are disclosed. The apparatus includes a rotor shaft coupled the bladed rotor of the aircraft and driven by a turbine shaft of the engine via a speed-reducing gear train. A speed-augmenting power transfer device has an input coupled to the rotor shaft and an output for outputting a rotation speed higher than a rotation speed of the rotor shaft received at the input of the speed-augmenting power transfer device. An electric generator disposed in a hub of the bladed rotor is coupled to the output of the speed-augmenting power transfer device and configured to generate electrical power for the device associated with the bladed rotor.
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公开(公告)号：US20170334377A1
公开(公告)日：2017-11-23
申请号：US15590554
申请日：2017-05-09
CPC分类号： B60R16/03 , B64D27/10 , F01D15/10 , F01D17/02 , F01D17/24 , F02C3/04 , F02C3/10 , F02C7/06 , F02C7/275 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2220/323 , F05D2220/36 , F05D2220/76 , H02K5/1732 , H02K7/1823 , H02K9/19 , H02K2203/09 , H02P9/04
摘要： A gas turbine engine and methods of operation include a low pressure electric motor-generator having an electrical assembly for electrical connection.
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公开(公告)号：US20170320585A1
公开(公告)日：2017-11-09
申请号：US15440480
申请日：2017-02-23
CPC分类号： B64D31/00 , B64D27/10 , B64D27/24 , B64D31/06 , B64D2027/026 , F02C7/32 , Y02T50/44 , Y02T50/64 , Y10S903/905 , Y10S903/93
摘要： The disclosure is directed to an optionally hybrid power system that may operate either as a traditional power system, deriving power from a single power source, or as a hybrid power system, deriving power from multiple types of power sources. An example optionally hybrid power system may include a gas turbine engine and one or more electric motors. When configured as a traditional power system the optionally hybrid power system may derive all power from the gas turbine engine. However, when configured as a hybrid power system, the one or more motors may be coupled to the optionally hybrid power system to supplement the power produced by the gas turbine engine. Additionally, an operator interface that may control the optionally hybrid power system may select from a plurality of operating modes that depend on the configuration of the optionally hybrid power system.
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