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公开(公告)号：US12044194B2
公开(公告)日：2024-07-23
申请号：US16811368
申请日：2020-03-06
发明人： David Marion Ostdiek , Alan Roy Stuart , Daniel Alan Niergarth , Gert Johannes van der Merwe , Brandon Wayne Miller , Stephen William Freund
摘要： A propulsion system, the propulsion system comprising a rotating element, a stationary element, and an inlet between the rotating element and the stationary element, wherein the inlet passes radially inward of the stationary element; wherein the inlet passes radially inward of the stationary element; wherein the inlet leads to an inlet duct containing a ducted fan having an axis of rotation and a plurality of blades; and wherein the inlet duct divides into a first duct and a second duct, separate from the first duct. A method of operating a propulsion system, comprising the steps of: operating a first rotating fan assembly to produce a first stream of air; directing a portion of the first stream of air into a second ducted rotating fan assembly; operating the second ducted rotating fan assembly to produce a second stream of air; dividing the second stream of air into a core stream and a fan stream; and directing the core stream into a gas turbine engine core.
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公开(公告)号：US11885267B2
公开(公告)日：2024-01-30
申请号：US17578806
申请日：2022-01-19
申请人： GE Avio S.r.l.
发明人： Paolo Altamura , Michele Gravina
CPC分类号： F02C7/36 , F02C7/06 , F02K3/072 , F05D2240/52 , F05D2260/40311
摘要： A gas turbine engine includes a fan assembly having a plurality of fan blades; and a turbomachine. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbomachine further including a first input power source; a second input power source configured to counter-rotate relative to the first input power source; a power output component operably connected to the fan assembly; and a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear.
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公开(公告)号：US20230203985A1
公开(公告)日：2023-06-29
申请号：US18001418
申请日：2021-06-01
CPC分类号： F02C3/067 , F01D1/24 , F01D25/162 , F02C7/06 , F02K3/072 , F05D2250/44
摘要： Counter-rotating turbine of a turbomachine extending about an axis of rotation and comprising an inner rotor having 5 at least one inner moving blade supported in rotation by a first shaft, an outer rotor rotating in an opposite direction to the inner rotor, and comprising at least one outer moving blade supported in rotation by a second shaft coaxial with the first shaft, the first 10 and second shafts extending axially from upstream to downstream of the turbine, the first shaft being guided in rotation by a first bearing disposed between the first shaft and an upstream casing of the turbine, and the second shaft being guided in rotation by a second bearing disposed between the second 15 shaft and said upstream casing of the turbine, the first bearing and the second bearing being disposed upstream of a first stage of the inner rotor.
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公开(公告)号：US11680486B2
公开(公告)日：2023-06-20
申请号：US16779712
申请日：2020-02-03
申请人： ROLLS-ROYCE plc
CPC分类号： F01D1/26 , F01D15/10 , F01D15/12 , F02K3/072 , F04D19/024 , H02K7/1823 , F05D2250/44 , F05D2260/40311
摘要： Turbomachinery comprising first and second sets of rotors configured to operate on a working fluid. The machinery further comprises first and second sets of electric machines coupled to the respective first and second rotors, and a coupling arrangement arranged to couple adjacent rotors of the first and second rotor sets to provide for fixed ratio, contra-rotation of the first and second rotor sets.
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公开(公告)号：US20230048465A1
公开(公告)日：2023-02-16
申请号：US17578806
申请日：2022-01-19
申请人： GE Avio S.r.l.
发明人： Paolo Altamura , Michele Gravina
摘要： A gas turbine engine includes a fan assembly having a plurality of fan blades; and a turbomachine. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbomachine further including a first input power source; a second input power source configured to counter-rotate relative to the first input power source; a power output component operably connected to the fan assembly; and a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear.
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公开(公告)号：US11485506B2
公开(公告)日：2022-11-01
申请号：US15745691
申请日：2016-07-21
IPC分类号： B64D27/20 , F04D29/68 , F01D17/16 , F04D29/54 , F01D9/06 , F02K3/062 , F04D29/56 , B64D29/04 , B64D33/02 , F02K3/072
摘要： An aircraft including a fuselage and a propulsion assembly. The propulsion assembly includes at least one fan rotor placed behind the fuselage as an extension thereof along a longitudinal axis, and a nacelle which forms a fairing of the at least one fan rotor through which at least one air flow passes. The aircraft comprises a plurality of stator radial arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle. The radial arms comprise at least one variable-pitch movable portion configured to axially divert the air flow.
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公开(公告)号：US11313327B2
公开(公告)日：2022-04-26
申请号：US16528114
申请日：2019-07-31
申请人： ROLLS-ROYCE plc
发明人： Giles E Harvey
IPC分类号： F02K3/072
摘要： An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. The outer fan has a diameter of from 2.5 to 3.5 times a diameter of the inner fan.
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公开(公告)号：US11193496B2
公开(公告)日：2021-12-07
申请号：US16740817
申请日：2020-01-13
发明人： Edward J. Gallagher , Lisa I. Brilliant , Joseph C. Straccia , Stanley J. Balamucki , Mark A. Stephens , Kate Hudon
摘要： A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle within the range of 80% span to 100% span. The camber angle is less than 20° within the entire range of 40% span to 100% span.
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公开(公告)号：US11118506B2
公开(公告)日：2021-09-14
申请号：US16229533
申请日：2018-12-21
发明人： Bhaskar Nanda Mondal
摘要： A gear assembly for a turbo machine is provided. The gear assembly includes a first input shaft, a second input shaft, an output shaft, a fixed member, and a spindle. The spindle is extended along a spindle centerline axis. The first input shaft is drivingly connected to the spindle at a first interface. The second input shaft is drivingly connected to the spindle at a second interface. The spindle is connected to the fixed member providing a reactive force at a third interface. The spindle is connected to the output shaft at a fourth interface.
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公开(公告)号：US11060527B2
公开(公告)日：2021-07-13
申请号：US15337936
申请日：2016-10-28
发明人： Bronwyn Power , Jonathan M. Rivers
IPC分类号： F04D29/32 , F02K3/072 , F02C9/58 , F01D5/14 , F02K3/04 , F01D5/22 , B64C11/00 , B64C11/48 , F04D19/00 , F04D29/02 , B64D27/00
摘要： A fan system includes a rotor having plurality of blades and a ring airfoil, the plurality of blades being rotatably joined to a hub and the ring airfoil. The fan system may include a second contra-rotationally disposed rotor having a plurality of blades and a ring airfoil. The first and second ring airfoils having a cambered shape and an angle of attack between about −5 degrees and about 45 degrees. Passive leading edge slats are attached to the ring airfoil and are configured to open and close using springs.
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