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公开(公告)号：US20240301805A1
公开(公告)日：2024-09-12
申请号：US18181149
申请日：2023-03-09
发明人： Paul M. Lutjen , Dairus D. McDowell
CPC分类号： F01D25/243 , F01D9/023 , F05D2240/40 , F05D2260/36
摘要： A component of a gas turbine engine includes a continuous hoop portion extending at least partially around an engine central longitudinal axis of the gas turbine engine and a bolting feature extending from the hoop portion, configured for securing the component to an adjacent component. The bolting feature includes a circumferential arm extending radially and circumferentially from the hoop portion. The circumferential arm defines a radial gap between the circumferential arm and the hoop portion. The circumferential arm includes a bolt opening for installation of a bolt therethrough. A connecting leg extends radially from the hoop portion across the radial gap toward the connecting arm. An arm interlocking feature is located at the circumferential arm and is configured to radially interlock with a complementary leg interlocking feature of the connecting leg. The arm interlocking feature and the leg interlocking feature have a radial interconnect gap therebetween in a free state.
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2.发明授权公开(公告)号：US11898504B2
公开(公告)日：2024-02-13
申请号：US17132066
申请日：2020-12-23
CPC分类号： F02C9/40 , E21B43/2607 , F02C7/222 , F02C7/232 , F05D2210/11 , F05D2210/12 , F05D2220/32 , F05D2240/35 , F05D2240/40 , F05D2260/60
摘要： Embodiments of systems and methods for air recovery are disclosed. The diverted pressurized air may be used to supply a hydrostatic purge to the unutilized portion of a turbine engine fuel manifold circuit to ensure that exhaust gases from the utilized side of the fuel manifold circuit do not enter the portion of the alternative fuel manifold circuit rack. The assembly used to remove compressor section pressurized air may include a flow control orifice, line pressure measuring instrumentation, non-return valves, isolation valves and hard stainless-steel tubing assemblies. In some embodiments, a turbine compressor section diverter system may include a small air receiver used to increase the volume of air supplying the manifold to aid in potential pressure and flow disruptions from a turbine engine compressor section.
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公开(公告)号：US11846253B2
公开(公告)日：2023-12-19
申请号：US17286623
申请日：2018-10-30
发明人： Yaping (Alan) Huang
CPC分类号： F02K9/52 , F02K9/60 , F23R3/34 , F23R3/343 , F23R3/346 , F23R3/58 , F05D2240/40 , F05D2250/37
摘要： An injector for a liquid rocket engine includes an array of injector elements. Each injector element includes a central passage and a plurality of peripheral transverse passages. The central passages are configured to provide axial injection flow and the peripheral transverse passages are configured to provide swirl injection flow about the axial injection flow. A portion of the injector elements are configured to provide the swirl injection flow in a clockwise direction and another portion of the injector elements are configured to provide the swirl injection flow in a counter-clockwise direction. The injector elements are arranged to form a plurality of circumferential rows. The injector elements of each individual circumferential row are either all of the clockwise direction or all of the counter-clockwise direction. At least one of the circumferential rows is of the clockwise direction and at least one of the circumferential rows is of the counter-clockwise direction.
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公开(公告)号：US20180266316A1
公开(公告)日：2018-09-20
申请号：US15764864
申请日：2016-10-05
发明人： Laurent SOULAT , Kevin Morgane LEMARCHAND , Tewfik BOUDEBIZA , Gilles Alain CHARIER , Nathalie NOWAKOWSKI , Augustin Marc Michel CURLIER , Adrien Pierre Jean PERTAT , Pierre-Alain Jean Philippe REIGNER
CPC分类号： F02C3/10 , B64D27/12 , B64D27/18 , B64D27/26 , B64D35/04 , B64D2027/266 , F01D15/12 , F02C3/107 , F02C7/36 , F02K3/06 , F02K3/062 , F05D2220/323 , F05D2220/36 , F05D2240/14 , F05D2240/40 , F05D2240/60 , F05D2250/312 , F05D2260/40311
摘要： The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY′) offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.
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公开(公告)号：US20180245541A1
公开(公告)日：2018-08-30
申请号：US15962039
申请日：2018-04-25
IPC分类号： F02K3/06 , F02C7/36 , F02K3/072 , F01D9/04 , F02C9/18 , F01D5/06 , F01D9/02 , F02C3/04 , F02K1/78 , F04D27/00 , F04D29/32 , F02C3/107 , F01D25/16 , F02C7/06 , F01D5/02
CPC分类号： F02K3/06 , F01D5/02 , F01D5/06 , F01D9/02 , F01D9/041 , F01D25/164 , F02C3/04 , F02C3/107 , F02C7/06 , F02C7/36 , F02C9/18 , F02K1/78 , F02K3/072 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2250/30 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
摘要： A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.
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公开(公告)号：US20180156135A1
公开(公告)日：2018-06-07
申请号：US15875656
申请日：2018-01-19
发明人： William G. Sheridan , Karl L. Hasel
CPC分类号： F02C7/32 , F02C3/04 , F02C3/06 , F02C3/107 , F02C3/113 , F02C7/00 , F02C7/36 , F05D2210/12 , F05D2220/32 , F05D2220/36 , F05D2240/40 , F05D2260/40311 , F16H1/28 , F16H1/36
摘要： A gas turbine engine includes a fan with a plurality of fan blades rotatable about an engine centerline longitudinal axis. The fan has a low corrected fan tip speed less than 1400 ft/sec. A bypass ratio is greater than 13 and less than 20. A fan pressure ratio less than 1.48. A speed reduction device comprises a gear system with a gear ratio of at least 2.6 and less than or equal to 4.1. A low and high pressure turbine is in communication with a first and second shaft, respectively. The low pressure turbine includes at least three stages and no more than four stages. The high pressure turbine includes two stages. The gear ratio is configured such that in operation the fan blade does not exceed a fan tip speed boundary condition or a second stress level. A low pressure turbine rotor does not exceed a first stress level.
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公开(公告)号：US09982627B2
公开(公告)日：2018-05-29
申请号：US14445360
申请日：2014-07-29
CPC分类号： F02K1/70 , F01D9/041 , F01D17/105 , F01D25/24 , F02K1/72 , F02K1/763 , F05D2220/32 , F05D2220/36 , F05D2240/12 , F05D2240/129 , F05D2240/40 , F05D2250/62 , F05D2260/50
摘要： A thrust reverser unit (TRU) 100 for a gas turbine engine 10 is provided that has first and second cascade elements 110, 120. In a stowed configuration, both the first and second cascade elements, and the operating mechanism, are located inside the nacelle 40, meaning that the TRU has no detrimental impact on the flow through the bypass duct 22. In the deployed configuration, the first cascade element 110 extends across the bypass duct 22. The first cascade element 110 has flow passages 112 that allow the flow to pass through, redirecting the flow towards the second cascade element 120. The second cascade element 120 further turns the flow so as to provide decelerating reverse thrust.
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公开(公告)号：US20180080373A1
公开(公告)日：2018-03-22
申请号：US15268713
申请日：2016-09-19
发明人： Daniel Bernard Kupratis , Tania Bhatia Kashyap , Mark F. Zelesky , Arthur W. Utay , Gabriel L. Suciu , Thomas N. Slavens , Kevin L. Rugg , Brian Merry
CPC分类号： F02C3/107 , F02C3/145 , F02C7/04 , F05D2240/40 , F05D2250/30
摘要： A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.
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公开(公告)号：US09879612B2
公开(公告)日：2018-01-30
申请号：US14971680
申请日：2015-12-16
发明人： Lewis Berkley Davis, Jr. , Scott Arthur Day , Timothy Andrew Healy , Rebecca Kathryn Jaiven , Harold Lamar Jordan, Jr. , Rex Allen Morgan
CPC分类号： F02C9/28 , F02C9/00 , F05D2220/32 , F05D2240/40 , F05D2270/082 , F05D2270/71 , G05B2219/41108
摘要： Commanding GTs to base load level based upon measured ambient condition for each GT; commanding each GT to adjust a power output to match scaled power output value equal to a fraction of a difference between the respective power output and a nominal power output value, and measuring actual emissions value for each GT during the adjusting of the respective power output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value, a nominal emissions value at the ambient condition and an emissions scale factor, wherein the nominal emissions value at the ambient condition and the emissions scale factor are stored in a pre-existing emissions model for the GT.
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公开(公告)号：US09878796B2
公开(公告)日：2018-01-30
申请号：US14620259
申请日：2015-02-12
发明人： William G. Sheridan
CPC分类号： B64D27/24 , B64D35/02 , B64D35/04 , B64D2027/026 , F01D15/12 , F02C7/36 , F02K3/077 , F05D2220/323 , F05D2220/36 , F05D2240/40 , F05D2250/312 , F05D2260/4023 , F05D2260/4031 , Y02T50/62 , Y10S903/903
摘要： A gas turbine engine has a fan drive turbine for selectively driving a fan rotor. A drive shaft between the fan drive turbine and the fan rotor includes a clutch, and an electric motor. The electric motor is positioned such that it is not downstream of a flow path relative to the fan drive turbine. A method of operating a gas turbine engine is also disclosed.
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