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公开(公告)号：US20180354632A1
公开(公告)日：2018-12-13
申请号：US15619673
申请日：2017-06-12
CPC分类号： B64D27/24 , B64D27/02 , B64D27/10 , B64D31/02 , B64D31/06 , B64D35/08 , B64D2027/026 , F01D15/10 , F02C6/00 , F02C6/14 , F02C7/262 , F02C7/268 , F02C7/36 , F02K5/00 , F05D2220/76
摘要： A hybrid-electric propulsion system for an aircraft includes a propulsor and a turbomachine. The turbomachine includes a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool. The hybrid electric propulsion system further includes an electrical system including a first electric machine, a second electric machine, and an electric energy storage unit electrically connectable to the first and second electric machines. The first electric machine is coupled to the high pressure spool of the turbomachine and the second electric machine is coupled to the propulsor for driving the propulsor to provide a propulsive benefit for the aircraft. The hybrid electric propulsion system also includes a controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine.
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公开(公告)号：US20180281931A1
公开(公告)日：2018-10-04
申请号：US15475401
申请日：2017-03-31
发明人： Brandon Wayne Miller , Randy M. Vondrell , Patrick Michael Marrinan , Paul Robert Gemin , Nicholas Taylor Moore
CPC分类号： B64C21/06 , B64C2230/04 , B64D27/18 , B64D27/24 , B64D2027/026 , B64D2221/00 , F01D15/10 , F02K5/00 , F05D2220/36
摘要： An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole P = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.
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公开(公告)号：US20180238236A1
公开(公告)日：2018-08-23
申请号：US15747210
申请日：2016-07-22
发明人： Clarice CARMONE , Nicola BANCHI , Giuseppe IURISCI
CPC分类号： F02C7/143 , F01D5/066 , F02K5/00 , F04D17/122 , F04D29/284 , F05D2220/72 , F05D2260/211 , F25J3/0219 , F25J3/0238 , F25J2210/12 , F25J2215/62 , F25J2220/02 , F25J2230/20 , F25J2230/22 , F25J2230/30 , F25J2240/70
摘要： A charge gas compression train for ethylene, including on the same shaft line a steam turbine and a first compressor including a first group of compression stages, a second group of compression stages and a third group of compression stages, the first group of compression stages including an outlet configured to be connected to a first intercooler inlet, the second group of compression stages including a second compressor inlet configured to be connected to a first intercooler outlet, the second group of compression stages including a second compressor outlet configured to be connected to a second intercooler inlet, the third group of compression stages including a third compressor inlet configured to be connected to a second intercooler outlet; the first, the second and the third group of compression stages being integrated in a first common casing and operating at the same rotation speed of the steam turbine; the first compressor including a plurality of unshrouded and shrouded impellers, wherein at least an unshrouded impeller is positioned upstream to at least a shrouded impeller.
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公开(公告)号：US20180230845A1
公开(公告)日：2018-08-16
申请号：US15430052
申请日：2017-02-10
CPC分类号： F01D15/10 , B64C11/30 , B64D27/18 , B64D27/24 , B64D2027/026 , F02C6/00 , F02C6/14 , F02C7/32 , F02C7/36 , F02K3/06 , F02K5/00 , F05D2220/323 , F05D2220/36 , F05D2220/76
摘要： A propulsion system for an aircraft includes a turbomachine, a primary fan, and an electric machine. The turbomachine includes a first turbine and a second turbine, with at least one of the first turbine or second turbine operably connected to the electric machine and the second turbine driving the primary fan. The propulsion system additionally includes an auxiliary propulsor assembly configured to be mounted at a location away from the turbomachine and the primary fan. The electric machine is in electrical communication with the auxiliary propulsor assembly for transferring power with the auxiliary propulsor assembly during operation of the propulsion system.
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公开(公告)号：US09797297B2
公开(公告)日：2017-10-24
申请号：US14806918
申请日：2015-07-23
发明人： Jean Thomassin , Sebastien Bolduc , Bruno Villeneuve , Stephane Berube , Mike Fontaine , David Gagnon-Martin , Andre Julien , Mark Cunningham , Serge Lafortune , Pierre-Yves Legare
IPC分类号： F02B29/04 , F01C1/22 , F01C11/00 , F02B33/34 , F02B41/10 , F02B61/04 , F01D13/00 , F02K5/00 , F02C6/12 , F02B53/00
CPC分类号： F02B29/0493 , F01C1/22 , F01C11/002 , F01C11/008 , F01D13/003 , F02B29/0412 , F02B29/0418 , F02B33/34 , F02B41/10 , F02B53/00 , F02B61/04 , F02B2053/005 , F02C6/12 , F02K5/00 , F05D2220/40 , Y02T10/146 , Y02T10/163 , Y02T10/17
摘要： A compound engine assembly including an air conduit having an inlet in fluid communication with ambient air around the compound engine assembly, a compressor having an inlet in fluid communication with the air conduit, an engine core including at least one rotary internal combustion engine and having an inlet in fluid communication with an outlet of the compressor, a turbine section having an inlet in fluid communication with an outlet of the engine core and configured to compound power with the engine core; and at least one heat exchanger in fluid communication with the air conduit, each heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the air conduit circulating therethrough. A method of supplying air to a compound engine assembly is also discussed.
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公开(公告)号：US09476385B2
公开(公告)日：2016-10-25
申请号：US13674377
申请日：2012-11-12
申请人： The Boeing Company
发明人： Matthew D. Moore , Kelly L. Boren
CPC分类号： F02K5/00 , B64C11/001 , B64C11/18 , F01D1/24 , F01D5/03 , F01D5/225 , F02K1/44 , F02K1/827 , F02K3/062 , F02K3/072 , F04D29/326 , F05D2260/96 , Y02T50/672 , Y02T50/673 , Y10T137/0536
摘要： A propulsion system and methods are presented. A substantially tubular structure comprises a central axis through a longitudinal geometric center, and a first fan rotates around the central axis, and comprises a first fan hub and first fan blades. The fan hub is rotationally coupled to the substantially tubular structure, and the first fan blades are coupled to the first fan hub and increase in chord length with increasing distance from the first fan hub. A second fan is rotationally coupled to the substantially tubular structure and rotates around the central axis and contra-rotates relative to the first fan. Second fan blades are coupled to the second fan hub, and a nacelle circumscribing the first fan and the second fan is coupled to and rotates with the first fan.
摘要翻译： 提出了推进系统和方法。 基本上管状结构包括通过纵向几何中心的中心轴线，第一风扇围绕中心轴线旋转，并且包括第一风扇轮毂和第一风扇叶片。 风扇轮毂旋转地联接到基本上管状的结构，并且第一风扇叶片联接到第一风扇轮毂并随着与第一风扇轮毂的距离增加而增加弦长。 第二风扇旋转地联接到基本上管状的结构并围绕中心轴线旋转并相对于第一风扇反转。 第二风扇叶片联接到第二风扇轮毂，并且包围第一风扇和第二风扇的机舱联接到第一风扇并与第一风扇一起旋转。
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公开(公告)号：US20160076446A1
公开(公告)日：2016-03-17
申请号：US14856834
申请日：2015-09-17
CPC分类号： F02C6/14 , F02C6/20 , F02C6/206 , F02K3/06 , F02K5/00 , F05D2220/323 , F05D2220/64 , F05D2220/76
摘要： A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.
摘要翻译： 一种推进发动机，包括至少第一推进单元，其包括由齿轮环包围的第一风扇和驱动连接到第一风扇的第一轴的燃气涡轮发动机，至少第二推进单元，包括由齿轮环连接的第二风扇， 到可操作地耦合到电机的第二轴和连接到电机的至少一个蓄电装置。 齿轮环被配置为在风扇之间传递扭矩，使得它们可以在它们被所述第一和第二轴中的至少一个驱动时结合（直接地或通过中间齿轮）旋转。 推进发动机被布置成用于控制由燃气涡轮发动机和/或用作电动机或发电机的电机供应到第一和第二风扇的组件的扭矩。
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公开(公告)号：US20140060005A1
公开(公告)日：2014-03-06
申请号：US13756140
申请日：2013-01-31
申请人： Richard H. Lugg
发明人： Richard H. Lugg
IPC分类号： F02C3/04
CPC分类号： F02C3/04 , F01D15/10 , F02C7/32 , F02K1/08 , F02K3/025 , F02K3/06 , F02K5/00 , F05D2270/172 , F05D2300/507 , H05H1/50
摘要： Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exoskeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture. Engine performance may be controlled across the entire desired flight envelope, whether subsonic, transonic or supersonic flight conditions.
摘要翻译： 本文所述的超音速磁性高级发电喷射式电动涡轮机（S-MAGJET）以及亚音速导出装置MAGJET将气体动力涡轮机，超导电力和推进发电以及磁力通量场系统与离子等离子体环形喷射燃烧器 利用替代的石油基燃料和燃烧循环来创建用于航空航天推进的混合涡轮机涡轮机。 推进装置能够大幅提高马力，燃烧和推进效率，减轻重量。 此外，涡轮机械结构可以设置在外骨骼结构内，其实现了推力与重量比的增加，伴随着燃料效率和发电的增加。 引擎使用电磁功率管理系统架构连续调节温度，压力和质量气流要求。 发动机性能可以跨越整个所需的飞行范围进行控制，无论是亚音速，跨音速还是超音速飞行条件。
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公开(公告)号：US20130087661A1
公开(公告)日：2013-04-11
申请号：US13644980
申请日：2012-10-04
申请人： ROLLS-ROYCE PLC
摘要： This invention relates to a propulsive unit for an aircraft, comprising: a nacelle which defines a duct for channeling an airflow when in use and which provides an outwardly facing surface of the propulsive unit, the outwardly facing surface having an aerodynamic shape; a fan unit for accelerating the airflow within the duct when in use; wherein the duct has an inlet and an outlet and the nacelle is operable to adjust the either or both of the area of the inlet and outlet whilst substantially retaining the aerodynamic shape of the outwardly facing surface.
摘要翻译： 本发明涉及一种用于飞行器的推进单元，包括：机舱，其限定用于在使用时引导气流并且提供推进单元的面向外的表面的管道，面向外的表面具有空气动力学形状; 风扇单元，用于在使用时加速管道内的气流; 其中所述管道具有入口和出口，并且所述机舱可操作以调节所述入口和出口的所述区域中的一个或两者，同时基本上保持面向外的表面的空气动力学形状。
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公开(公告)号：US20110138765A1
公开(公告)日：2011-06-16
申请号：US13059240
申请日：2009-08-19
申请人： Richard H. Lugg
发明人： Richard H. Lugg
CPC分类号： F02C3/04 , F01D15/10 , F02C7/32 , F02K1/08 , F02K3/025 , F02K3/06 , F02K5/00 , F05D2270/172 , F05D2300/507 , H05H1/50
摘要： Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exo-skeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation over traditional gas turbine technology today. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture. Engine performance may be controlled across the entire desired flight envelope, whether subsonic, transonic or supersonic flight conditions. With bypass fan(s), compressor stages and turbine segments controlled electrically in a shaftless turbine design, the S-MAGJET maximizes the propulsion efficiencies over a broader range of operating conditions compared to current art of turbine technology and at much higher thermodynamic and aerodynamic efficiencies.
摘要翻译： 本文所述的超音速磁性高级发电喷射式电动涡轮机（S-MAGJET）以及亚音速导出装置MAGJET将气体动力涡轮机，超导电力和推进发电以及磁力通量场系统与离子等离子体环形喷射燃烧器 利用替代的石油基燃料和燃烧循环来创建用于航空航天推进的混合涡轮机涡轮机。 推进装置能够大幅提高马力，燃烧和推进效率，减轻重量。 此外，涡轮机械结构可以设置在外骨架结构中，其实现了随着传统燃气轮机技术的燃料效率和发电的同时增加，推力与重量比的增加。 引擎使用电磁功率管理系统架构连续调节温度，压力和质量气流要求。 发动机性能可以跨越整个所需的飞行范围进行控制，无论是亚音速，跨音速还是超音速飞行条件。 利用旁通风扇，压缩机级和涡轮机段在无轴式涡轮机设计中进行电气控制，与现有技术的涡轮技术相比，S-MAGJET在更宽的工作条件范围内最大限度地提高了推进效率，并具有更高的热力学和空气动力学效率 。
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