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公开(公告)号：US12116928B2
公开(公告)日：2024-10-15
申请号：US18185007
申请日：2023-03-16
发明人： David Menheere
CPC分类号： F02C3/085 , F02C6/20 , F02C3/045 , F02C3/08 , F02C3/09 , F02C3/10 , F02C3/103 , F02C3/107 , F02C3/13 , F02C7/36
摘要： An aircraft engine, has: a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor; and a low-pressure spool having: a first low-pressure turbine downstream of the high-pressure turbine; and a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine.
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公开(公告)号：US11898429B2
公开(公告)日：2024-02-13
申请号：US18138319
申请日：2023-04-24
IPC分类号： E21B43/26 , F02C9/20 , F02C7/32 , F04B17/05 , F04B49/10 , F04B49/20 , F02C7/36 , F02C3/10 , F02C7/268 , F04B49/08
CPC分类号： E21B43/2607 , F02C3/10 , F02C7/268 , F02C7/32 , F02C7/36 , F02C9/20 , F04B17/05 , F04B49/08 , F04B49/103 , F04B49/20 , F05D2270/02 , F05D2270/052
摘要： Systems and methods to pump fracturing fluid into a wellhead may include a gas turbine engine including a compressor turbine shaft connected to a compressor, and a power turbine output shaft connected to a power turbine. The compressor turbine shaft and the power turbine output shaft may be rotatable at different rotational speeds. The systems may also include a transmission including a transmission input shaft connected to the power turbine output shaft and a transmission output shaft connected to a hydraulic fracturing pump. The systems may also include a fracturing unit controller configured to control one or more of the rotational speeds of the compressor turbine shaft, the power turbine output shaft, or the transmission output shaft based at least in part on target signals and fluid flow signals indicative of one or more of pressure or flow rate associated with fracturing fluid pumped into the wellhead.
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公开(公告)号：US11885252B2
公开(公告)日：2024-01-30
申请号：US16006327
申请日：2018-06-12
申请人： RTX CORPORATION
IPC分类号： F01D25/16 , F01N3/20 , F01D25/18 , F02C3/10 , F02K3/06 , F02C7/36 , F02C7/06 , F02C7/10 , F01N11/00 , F16N7/34
CPC分类号： F01N3/208 , F01D25/16 , F01D25/18 , F01N3/2066 , F01N11/00 , F02C3/10 , F02C7/06 , F02C7/10 , F02C7/36 , F02K3/06 , F01N2610/01 , F01N2610/02 , F01N2610/142 , F01N2610/1406 , F01N2610/148 , F01N2900/1814 , F05D2260/40311 , F16N7/34 , Y02T10/12 , Y02T50/60 , Y10T29/4932 , Y10T137/0324 , Y10T137/7297
摘要： In an embodiment of the present disclosure, a gas turbine engine includes a fan, a first compressor stage and a second compressor stage, a first turbine stage and a second turbine stage, and wherein said first turbine stage drives said second compressor stage as a high spool, and wherein said second turbine stage drives said first compressor stage as part of a low spool, and a gear train driving said fan with said low spool, and such that said fan and said first compressor stage rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool.
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公开(公告)号：US11840958B2
公开(公告)日：2023-12-12
申请号：US17393508
申请日：2021-08-04
申请人： RTX Corporation
摘要： A gas turbine engine includes a fan positioned at an engine central longitudinal axis, and a fan drive turbine located at the engine central longitudinal axis and configured to drive rotation of the fan. A gas generator is non-coaxial with the fan drive turbine and operably connected to the fan drive turbine such that exhaust from the gas generator drives rotation of the fan drive turbine. An auxiliary power core is located at the engine central longitudinal axis, and one or more bleed passages connect the gas generator and the auxiliary power core. The one or more bleed passages are configured to selectably combine a bleed airflow from the gas generator and an auxiliary core airflow at the auxiliary power core to direct the combined airflow to the fan drive turbine to increase output of the fan drive turbine.
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公开(公告)号：US20180347428A1
公开(公告)日：2018-12-06
申请号：US16006327
申请日：2018-06-12
IPC分类号： F01N3/20 , F02C7/10 , F02C7/36 , F01D25/16 , F01D25/18 , F02C7/06 , F01N11/00 , F02K3/06 , F02C3/10 , F16N7/34
CPC分类号： F01N3/208 , F01D25/16 , F01D25/18 , F01N3/2066 , F01N11/00 , F01N2610/01 , F01N2610/02 , F01N2610/1406 , F01N2610/142 , F01N2610/148 , F01N2900/1814 , F02C3/10 , F02C7/06 , F02C7/10 , F02C7/36 , F02K3/06 , F05D2260/40311 , F16N7/34 , Y02T10/24 , Y02T50/671 , Y10T29/4932 , Y10T137/0324 , Y10T137/7297
摘要： In an embodiment of the present disclosure, a gas turbine engine includes a fan, a first compressor stage and a second compressor stage, a first turbine stage and a second turbine stage, and wherein said first turbine stage drives said second compressor stage as a high spool, and wherein said second turbine stage drives said first compressor stage as part of a low spool, and a gear train driving said fan with said low spool, and such that said fan and said first compressor stage rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool.
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公开(公告)号：US10036316B2
公开(公告)日：2018-07-31
申请号：US14663727
申请日：2015-03-20
CPC分类号： F02C3/13 , F02C3/06 , F02C3/10 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/24 , F05D2240/30 , F05D2240/35 , F05D2240/55 , F05D2250/283 , F05D2260/40311 , Y02T50/671
摘要： A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000° F. and about 1500° F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.
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7.发明申请公开(公告)号：US20180187604A1
公开(公告)日：2018-07-05
申请号：US15129240
申请日：2015-03-26
IPC分类号： F02C7/275 , B64C27/12 , B64D35/02 , B64D35/08 , F02C3/107 , F02C3/10 , F02C7/262 , F02C9/42 , F02C7/32 , H02K7/20 , H02K7/18
CPC分类号： F02C7/275 , B64C27/12 , B64D35/02 , B64D35/08 , F02C3/10 , F02C3/107 , F02C7/262 , F02C7/32 , F02C7/36 , F02C9/42 , F05D2220/329 , F05D2220/76 , H02K7/1823 , H02K7/20 , Y02T50/671
摘要： An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.
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公开(公告)号：US09982629B2
公开(公告)日：2018-05-29
申请号：US15185498
申请日：2016-06-17
发明人： Michael J. Armstrong , Igor Vaisman
IPC分类号： F02C3/04 , F02C3/13 , F02C1/10 , F02C7/08 , F02K3/00 , F01K23/10 , F02K3/077 , F02C1/00 , F02C6/20 , F02C7/141 , F02C7/18 , F02C3/10 , F02K99/00 , F22B3/08 , F02C7/143 , F01K25/10
CPC分类号： F02K3/00 , F01K23/10 , F01K25/103 , F02C1/007 , F02C1/10 , F02C3/04 , F02C3/10 , F02C3/13 , F02C6/206 , F02C7/08 , F02C7/141 , F02C7/143 , F02C7/18 , F02K3/077 , F02K99/00 , F05D2210/10 , F05D2210/13 , F05D2250/311 , F05D2260/213 , F22B3/08 , Y02T50/676
摘要： A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.
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公开(公告)号：US09982555B2
公开(公告)日：2018-05-29
申请号：US15116706
申请日：2014-03-14
申请人： Hitachi, Ltd.
发明人： Aung Ko Thet , Noriaki Hino , Naohiro Kusumi
CPC分类号： F01D15/10 , F01D5/02 , F02C3/10 , F02C6/14 , F05D2220/32 , F05D2220/76 , F05D2240/60 , F05D2270/06 , H02K7/1823
摘要： A gas turbine power generation system has a dual-shaft gas turbine, an electric generator mechanically connected to a low pressure turbine of the dual-shaft gas turbine and electrically connected to an electric power system, a rotary electric machine mechanically connected to a high pressure turbine through a compressor of the dual-shaft gas turbine and electrically connected to the electric power system, and an electric power output from the electric generator side to the electric power system is adjusted by operation of the rotary electric machine as a motor or as a generator.
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公开(公告)号：US09970323B2
公开(公告)日：2018-05-15
申请号：US14427664
申请日：2013-03-14
CPC分类号： F01D25/24 , F01D25/243 , F02C3/10 , F02C6/08 , F02C7/36 , F05D2250/30 , F05D2260/40311
摘要： A gas turbine engine has a compressor section, a compressor case substantially surrounding the compressor section, and a diffuser case attached at an attachment interface to the compressor case. The attachment interface is between a forward and an aft end of the compressor. A geared turbofan is also disclosed.
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