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1. 发明授权

US07753036B2 Compound cycle rotary engine 有权
标题翻译：复合循环旋转发动机
公开(公告)号：US07753036B2
公开(公告)日：2010-07-13
申请号：US11824645
申请日：2007-07-02
申请人： Charles E. Lents , Stephen P. Zeppieri , Roy N. Guile , Vincent C. Nardone , Jonathan Lauter , Arindam Dasgupta
发明人： Charles E. Lents , Stephen P. Zeppieri , Roy N. Guile , Vincent C. Nardone , Jonathan Lauter , Arindam Dasgupta
IPC分类号： F02B33/00
CPC分类号： F01C11/008 , F01C1/22 , F02B29/0437 , F02B37/00 , F02B41/10 , F02B53/04 , F02B2275/32 , Y02T10/142 , Y02T10/144 , Y02T10/163 , Y02T10/17
摘要： A compound cycle engine system has a rotary engine, which rotary engine generates exhaust gas. The system further has a compressor for increasing the pressure of inlet air to be supplied to the engine to a pressure in the range of from 3.0 to 5.0 atmospheres and an intercooler for providing the inlet air to the engine at a temperature in the range of from 150 to 250 degrees Fahrenheit. The system further has one or more turbines for extracting energy from the exhaust gas. The Miller Cycle is implemented in the rotary engine, enabling the compression ratio to be lower than the expansion ratio, allowing the overall cycle to be optimized for lowest weight and specific fuel consumption.
摘要翻译：复合循环发动机系统具有旋转发动机，该旋转发动机产生废气。该系统还具有用于将供给发动机的入口空气的压力提高到3.0-5.0大气压的压缩机，以及用于在从...的范围内的温度下向发动机提供入口空气的中间冷却器 150至250华氏度。该系统还具有用于从废气中提取能量的一个或多个涡轮机。米勒循环在旋转发动机中实现，使压缩比低于膨胀比，从而可以优化整体循环，以获得最低的重量和特定的燃油消耗。

2. 发明申请

US20090007882A1 Compound cycle rotary engine 有权
标题翻译：复合循环旋转发动机
公开(公告)号：US20090007882A1
公开(公告)日：2009-01-08
申请号：US11824645
申请日：2007-07-02
申请人： Charles E. Lents , Stephen P. Zeppieri , Roy N. Guile , Vincent C. Nardone , Jonathan Lauter , Arindam Dasgupta
发明人： Charles E. Lents , Stephen P. Zeppieri , Roy N. Guile , Vincent C. Nardone , Jonathan Lauter , Arindam Dasgupta
IPC分类号： F02B53/02
CPC分类号： F01C11/008 , F01C1/22 , F02B29/0437 , F02B37/00 , F02B41/10 , F02B53/04 , F02B2275/32 , Y02T10/142 , Y02T10/144 , Y02T10/163 , Y02T10/17
摘要： A compound cycle engine system has a rotary engine, which rotary engine generates exhaust gas. The system further has a compressor for increasing the pressure of inlet air to be supplied to the engine to a pressure in the range of from 3.0 to 5.0 atmospheres and an intercooler for providing the inlet air to the engine at a temperature in the range of from 150 to 250 degrees Fahrenheit. The system further has one or more turbines for extracting energy from the exhaust gas. The Miller Cycle is implemented in the rotary engine, enabling the compression ratio to be lower than the expansion ratio, allowing the overall cycle to be optimized for lowest weight and specific fuel consumption.
摘要翻译：复合循环发动机系统具有旋转发动机，该旋转发动机产生废气。该系统还具有用于将供给发动机的入口空气的压力提高到3.0-5.0大气压的压缩机，以及用于在从...的范围内的温度下向发动机提供入口空气的中间冷却器 150至250华氏度。该系统还具有用于从废气中提取能量的一个或多个涡轮机。米勒循环在旋转发动机中实现，使压缩比低于膨胀比，从而可以优化整体循环，以获得最低的重量和特定的燃油消耗。

3. 发明申请

US20100313591A1 ADAPTIVE HEAT SINK FOR AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM 审中-公开
标题翻译：用于飞机环境控制系统的自适应散热器
公开(公告)号：US20100313591A1
公开(公告)日：2010-12-16
申请号：US12483764
申请日：2009-06-12
申请人： Charles E. Lents , Scott F. Kaslusky
发明人： Charles E. Lents , Scott F. Kaslusky
IPC分类号： F25B5/02 , F28F27/00 , F28D15/00
CPC分类号： F02C7/224 , B64D37/34 , F02C7/10
摘要： An avionics cooling system includes a first heat exchange system, a second heat exchange system and a vapor cycle system. The second heat exchange system has a heat sink capacity that is generally out of phase with a heat sink capacity of the first heat exchange system. The vapor cycle includes a fluid loop in communication with the first and second heat exchange systems and the fluid loop transfers heat to the first and second heat exchange systems. A method for cooling aircraft components includes selectively directing a fluid having an elevated temperature in a fluid loop of a vapor cycle system to a first heat exchanger to transfer heat from the fluid to a fuel based on a heat sink capacity of the fuel, selectively directing the fluid to a second heat exchanger to transfer heat from the fluid to air based on a heat sink capacity of the air, and cooling aircraft components with the fluid.
摘要翻译：航空电子冷却系统包括第一热交换系统，第二热交换系统和蒸气循环系统。第二热交换系统具有通常与第一热交换系统的散热能力相异的散热能力。蒸气循环包括与第一和第二热交换系统连通的流体回路，并且流体回路将热量传递到第一和第二热交换系统。用于冷却飞行器部件的方法包括将具有高温的流体在蒸气循环系统的流体回路中选择性地引导到第一热交换器，以基于燃料的散热器能力将热量从流体传递到燃料，流体到第二热交换器以基于空气的散热能力将热量从流体传递到空气，以及用流体冷却飞行器部件。

4. 发明申请

US20100170262A1 AIRCRAFT POWER AND THERMAL MANAGEMENT SYSTEM WITH ELECTRIC CO-GENERATION 审中-公开
标题翻译：具有电力发电的飞机功率和热管理系统
公开(公告)号：US20100170262A1
公开(公告)日：2010-07-08
申请号：US12349029
申请日：2009-01-06
申请人： Scott F. Kaslusky , Charles E. Lents
发明人： Scott F. Kaslusky , Charles E. Lents
IPC分类号： F02C7/275 , F02C6/08 , F02C7/26
CPC分类号： B64D13/00 , B64D33/00 , B64D41/00 , F01D15/10 , F02C7/32 , Y02E20/14 , Y02T50/44 , Y02T50/671
摘要： A power and thermal management system includes an integrated power package which receives bleed air, communicates conditioned air to an environmental control air distribution system and selectively communicates electrical power with an electrical distribution system.
摘要翻译：电力和热管理系统包括集成的功率封装，其接收放气，将调节空气与环境控制空气分配系统进行通信，并且与配电系统选择性地通信电力。

5. 发明申请

US20080209911A1 Combination engines for aircraft 有权
标题翻译：飞机组合发动机
公开(公告)号：US20080209911A1
公开(公告)日：2008-09-04
申请号：US11713262
申请日：2007-03-02
申请人： Frederick M. Schwarz , Brian M. Fentress , Andrew P. Berryann , Charles E. Lents , Jorn A. Glahn
发明人： Frederick M. Schwarz , Brian M. Fentress , Andrew P. Berryann , Charles E. Lents , Jorn A. Glahn
IPC分类号： F02C6/08
CPC分类号： F02K5/023 , F01D15/10 , F02C3/10 , F02C6/08 , F02K3/06 , F02K3/075
摘要： An engine combination for generating forces with a gas turbine engine generating force, and an internal combustion engine provided in the combination as an intermittent combustion engine generating force having an air intake, there being an air transfer duct connected from a compressor in the gas turbine engine to the air intake to transfer compressed air thereto.
摘要翻译：一种用于产生具有燃气涡轮发动机产生力的发动机组合，以及组合中设置的内燃机作为具有进气口的间歇式内燃机产生力，存在从燃气涡轮发动机中的压缩机连接的空气传送管道到空气入口以将压缩空气传送到其上。

6. 发明授权

US06845630B2 Electric power and cooling system for an aircraft 有权
标题翻译：飞机电力和冷却系统
公开(公告)号：US06845630B2
公开(公告)日：2005-01-25
申请号：US10077281
申请日：2002-02-14
申请人： Louis J. Bruno , Charles E. Lents , Michael K. Sahm , Wayne A. Thresher
发明人： Louis J. Bruno , Charles E. Lents , Michael K. Sahm , Wayne A. Thresher
IPC分类号： B64D13/06 , F25D9/00 , B64D13/02
CPC分类号： B64D13/06 , B64D2013/064 , B64D2013/0644 , Y02T50/56
摘要： The present invention relates to an electrical power and cooling system for use in an aircraft having at least one engine. The electrical power and cooling system comprises a single shaft, a power turbine mounted on the shaft for receiving fresh pressurized air from the at least one engine, a cooling turbine mounted on the shaft and receiving the fresh pressurized air from the at least one engine, a generator mounted on the shaft, and a fan mounted on the shaft for creating a flow of cooling air. The system further has a condenser for removing moisture from the air exiting the cooling turbine and a mixing chamber for mixing the cooled dry air with recirculated cabin air. The electrical power and cooling system delivers conditioned air to a cabin and/or a flight deck onboard the aircraft and electrical power to the aircraft's electrical systems.
摘要翻译：本发明涉及一种用于具有至少一个发动机的飞行器中的电力和冷却系统。电力和冷却系统包括单个轴，安装在轴上的动力涡轮机，用于接收来自至少一个发动机的新鲜加压空气;安装在轴上的冷却涡轮机，以及接收来自至少一个发动机的新鲜加压空气，安装在轴上的发电机和安装在轴上的风扇，用于产生冷却空气流。该系统还具有用于从离开冷却涡轮机的空气中除去水分的冷凝器和用于将冷却的干燥空气与再循环的机舱空气混合的混合室。电力和冷却系统向飞机上的舱室和/或飞行甲板提供调节空气，并向飞机的电气系统提供电力。

7. 发明授权

US06704625B2 Aircraft architecture with a reduced bleed aircraft secondary power system 有权
标题翻译：飞机架构与减少飞机二次电力系统
公开(公告)号：US06704625B2
公开(公告)日：2004-03-09
申请号：US10076898
申请日：2002-02-14
申请人： Jose Albero , Charles E. Lents , Michael K. Sahm , Richard C. Welch
发明人： Jose Albero , Charles E. Lents , Michael K. Sahm , Richard C. Welch
IPC分类号： B64B124
CPC分类号： F02C7/32 , B64D13/06 , B64D2013/0611 , B64D2013/0618 , B64D2013/064 , B64D2013/0644 , Y02T50/54 , Y02T50/56
摘要： The present invention relates to an improved architecture for an aircraft. The aircraft has a first engine, a first gearbox associated with the first engine, a first starter/generator associated with the gearbox, and a first motor drive connected to the first starter/generator for providing the starter/generator with electric power to start the first engine and to receive electric power from the starter/generator after the engine has been started to operate electrically driven systems onboard the aircraft. The aircraft preferably further has at least one other engine which has a gearbox and a starter/generator associated with it and at least a second motor drive connected to the starter/generator. The electrically driven systems operated by the motor drive(s) include an environmental control system, a wing anti-icing system, an aircraft control system, and the aircraft fuel system. The aircraft also includes an auxiliary power unit for supplying electrical power to at least the first motor drive for initiating operation of the first engine.
摘要翻译：本发明涉及一种用于飞机的改进的架构。飞机具有第一发动机，与第一发动机相关联的第一变速箱，与变速箱相关联的第一起动/发电机，以及连接到第一起动器/发电机的第一电动机驱动器，用于向起动器/发电机提供电力以启动第一发动机，并且在发动机起动之后从起动器/发电机接收电力来操作飞机上的电驱动系统。飞机优选地还具有至少一个其它发动机，其具有齿轮箱和与其相关联的起动器/发电机以及连接到起动器/发电机的至少第二马达驱动器。由电动机驱动器操作的电驱动系统包括环境控制系统，机翼防冰系统，飞机控制系统和飞机燃料系统。该飞机还包括辅助动力单元，用于向至少第一马达驱动器提供电力以启动第一发动机的操作。

8. 发明授权

US4805691A Cooling technique for compact electronics inverter 失效
标题翻译：紧凑型电子逆变器的冷却技术
公开(公告)号：US4805691A
公开(公告)日：1989-02-21
申请号：US944758
申请日：1986-12-22
申请人： Alex Cook , Charles E. Lents
发明人： Alex Cook , Charles E. Lents
IPC分类号： F28D15/02 , H01L23/427 , H05K7/20 , H01L23/42
CPC分类号： H01L23/427 , H01L2924/0002
摘要： A substrate with a heat producing electronic component is mounted directly on a heat dissipating structure. The heat dissipating structure has a closed chamber with adjacent condenser and evaporator sections and contains a supply of liquid cooling fluid with a predetermined vaporization temperature. The evaporator section is in heat transfer relation with the substrate and the electronic component thereon. A plurality of channels are strategically arranged in the surfaces bounding the chamber to move the cooling fluid by capillary action in a predetermined path between the condenser and evaporator sections in heat exchange relationship over the chamber walls to maintain the substrate at an acceptable temperature. A heat sink, in heat exchange relationship with the condenser section of the heat dissipating structure, maintains a temperature differential between the evaporator and condenser sections and assures that the condenser section is cooled sufficiently to condense the cooling fluid.
摘要翻译：具有发热电子部件的基板直接安装在散热结构上。散热结构具有封闭的腔室，其具有相邻的冷凝器和蒸发器部分，并且包含具有预定蒸发温度的液体冷却流体。蒸发器部分与基板和其上的电子部件传热关系。在包围室的表面中，策略性地布置多个通道，以在腔室壁之间以热交换关系的冷凝器和蒸发器部分之间的预定路径中的毛细管作用移动冷却流体，以将基板保持在可接受的温度。与散热结构的冷凝器部分的热交换关系的散热器保持蒸发器和冷凝器部分之间的温差，并确保冷凝器部分被充分冷却以冷凝冷却流体。

9. 发明申请

US20090065652A1 Aircraft combination engines exhaust thrust recovery 有权
标题翻译：飞机组合发动机排气推力恢复
公开(公告)号：US20090065652A1
公开(公告)日：2009-03-12
申请号：US11803432
申请日：2007-05-15
申请人： Frederick M. Schwarz , Brian M. Fentress , Charles E. Lents
发明人： Frederick M. Schwarz , Brian M. Fentress , Charles E. Lents
IPC分类号： B64D27/02 , F02C6/06 , F02G3/00 , F02B65/00 , F02B63/04
CPC分类号： F02K5/02 , F02B61/00 , F02B65/00 , F02B73/00 , F02C3/13 , F02C5/00 , F02C6/10 , F02C6/12 , F05D2220/50 , F05D2220/76
摘要： A gas turbine engine with a turbine with an exhaust manifold thereabout from which fluids can be transferred to the turbine and an air compressor having an air transfer duct extending therefrom so as to be capable to provide compressed air in that air transfer duct at one end thereof to the air intake of an internal combustion engine provided as an intermittent combustion engine. The air intake and an exhaust outlet are each coupled to combustion chambers therein and a rotatable output shaft is also coupled to those combustion chambers for generating force. The exhaust outlet has an exhaust transfer duct extending therefrom so as to have the intermittent combustion engine be capable to provide exhaust therefrom in that exhaust transfer duct at one end thereof, and the exhaust transfer duct being connected at an opposite end thereof to the exhaust manifold to be capable of transferring intermittent combustion engine exhaust thereto.
摘要翻译：一种具有涡轮机的燃气涡轮发动机，具有排气歧管，流体可从该排气歧管传递到涡轮机，以及具有从其延伸的空气传输管道的空气压缩机，以便能够在该空气传输管道的一端处提供压缩空气到作为间歇式内燃机设置的内燃机的进气口。进气口和排气出口各自连接到其中的燃烧室，并且可旋转输出轴也联接到那些燃烧室以产生力。排气出口具有从其延伸的排气传送管道，以便使间歇式内燃机能够在其一端处于该排气传送管道中提供排气，并且排气传送管道在其相对端连接到排气歧管能够将间歇的内燃机排气转移到其上。

10. 发明授权

US06817575B1 Integrated system for providing aircraft environmental control 有权
标题翻译：提供飞机环境控制的综合系统
公开(公告)号：US06817575B1
公开(公告)日：2004-11-16
申请号：US10251721
申请日：2002-09-20
申请人： Jules Ricardo Munoz , Luca Bertuccioli , Michael K. Sahm , Jay Fletcher , Charles E. Lents , Steven E. Squier , Richard Welch , Arthur Curtis Becker
发明人： Jules Ricardo Munoz , Luca Bertuccioli , Michael K. Sahm , Jay Fletcher , Charles E. Lents , Steven E. Squier , Richard Welch , Arthur Curtis Becker
IPC分类号： B64D1308
CPC分类号： B64D13/06 , B64D2013/0614
摘要： The present invention relates to an integrated enviromental control system for an aircraft. The system uses bleed air from a propulsion engine to drive an air turbine which provides power to at least one aircraft component such as an aircraft mounted accessory drive. The system uses the bleed air exiting the air turbine as an air source for the cabin and/or flight deck enviromental control system.
摘要翻译：本发明涉及一种用于飞行器的综合环境控制系统。该系统使用来自推进发动机的排气来驱动空气涡轮机，该空气涡轮机向诸如飞机安装的附件驱动器的至少一个飞行器部件提供动力。该系统使用离开空气涡轮机的排气作为客舱和/或驾驶舱环境控制系统的空气源。

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