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1. 发明授权

US07434765B2 Heat exchanger systems and associated systems and methods for cooling aircraft starter/generators 有权
标题翻译：热交换器系统及相关系统和方法，用于冷却飞机启动器/发电机
公开(公告)号：US07434765B2
公开(公告)日：2008-10-14
申请号：US11060184
申请日：2005-02-16
申请人： Edward Zielinski , Thomas M. Murray
发明人： Edward Zielinski , Thomas M. Murray
IPC分类号： B64D33/10
CPC分类号： F28D7/0066 , B64D13/00 , F28D1/0435 , F28D7/0083 , F28D2021/0021 , Y02T50/44 , Y02T50/56
摘要： Heat exchanger systems and associated systems and methods for cooling aircraft starters/generators are disclosed. A system in accordance with one embodiment includes a first fluid flow path for a first fluid, a second fluid flow path for a second fluid, and a third fluid flow path for a third fluid. The first and second flow paths are positioned proximate to the third flow path to transfer heat between the third fluid and both the first and second fluids. The third flow path is configured to allow a transfer of heat between the second and third fluids at a first transfer rate when the first fluid carries heat at a first rate, and at a second transfer rate different than the first transfer rate when the first fluid does not carry heat, or carries heat at a second rate less than the first rate. Accordingly, when the heat to be rejected by one fluid is decreased, the heat transfer rate for the remaining fluid can be increased.
摘要翻译：公开了用于冷却飞机起动器/发电机的热交换器系统和相关系统和方法。根据一个实施例的系统包括用于第一流体的第一流体流动路径，用于第二流体的第二流体流动路径和用于第三流体的第三流体流动路径。第一和第二流动路径定位成靠近第三流动路径，以在第三流体和第一和第二流体两者之间传递热量。第三流动路径被配置为当第一流体以第一速率承载热量时以第一流体的速率传递第二流体和第三流体之间的热量，并且当第一流体不携带热量，或以低于第一速率的第二速率承载热量。因此，当由一种流体排出的热量降低时，可以增加剩余流体的传热速率。

2. 发明授权

US09382013B2 Variably extending heat transfer devices 有权
标题翻译：可变延伸的热传递装置
公开(公告)号：US09382013B2
公开(公告)日：2016-07-05
申请号：US13289307
申请日：2011-11-04
申请人： Thomas M. Murray , Edward Zielinski
发明人： Thomas M. Murray , Edward Zielinski
IPC分类号： F28F27/00 , B64D33/12 , B64G1/50
CPC分类号： B64D33/12 , B64G1/506
摘要： A heat transfer device for installation in a system having a heat generating element within the system away from which heat is to be transferred is described. The heat transfer device includes a heat pipe having a first portion, a second portion, and a working fluid contained within the heat pipe for transferring heat from the first portion to the second portion. The first portion is disposed in proximity with the heat generating element. The second portion is coupled to the first portion. At least part of the second portion is disposed outside the system to dissipate heat from the heat generating element and the second portion may be variably extended outside the system.
摘要翻译：描述了一种用于安装在系统内的热传递装置，其中系统内的发热元件远离热量被传送。传热装置包括：热管，其具有第一部分，第二部分和包含在热管内的工作流体，用于将热量从第一部分传递到第二部分。第一部分设置在发热元件附近。第二部分耦合到第一部分。第二部分的至少一部分设置在系统外部以散发来自发热元件的热量，并且第二部分可以可变地延伸到系统外部。

3. 发明申请

US20130112374A1 HEAT TRANSFER DEVICES 有权
标题翻译：换热装置
公开(公告)号：US20130112374A1
公开(公告)日：2013-05-09
申请号：US13289307
申请日：2011-11-04
申请人： Thomas M. Murray , Edward Zielinski
发明人： Thomas M. Murray , Edward Zielinski
IPC分类号： F28D15/04 , F28F1/00
CPC分类号： B64D33/12 , B64G1/506
摘要： Heat transfer devices are described. In one example, a heat transfer device for installation in a system having a heat generating element within the system away from which heat is to be transferred is described. The heat transfer device includes a heat pipe having a first portion, a second portion, and a working fluid contained within the heat pipe for transferring heat from the first portion to the second portion. The first portion is disposed in proximity with the heat generating element. The second portion is coupled to the first portion. At least part of the second portion is disposed outside the system to dissipate heat from the heat generating element and the second portion may be variably extended outside the system.
摘要翻译：描述了传热装置。在一个示例中，描述了一种用于安装在系统内的传热装置，其中系统内的发热元件远离热量将被传送。传热装置包括：热管，其具有第一部分，第二部分和包含在热管内的工作流体，用于将热量从第一部分传递到第二部分。第一部分设置在发热元件附近。第二部分耦合到第一部分。第二部分的至少一部分设置在系统外部以散发来自发热元件的热量，并且第二部分可以可变地延伸到系统外部。

4. 发明授权

US07883053B2 Heat exchanger systems and associated systems and methods for cooling aircraft starter/generators 有权
标题翻译：热交换器系统及相关系统和方法，用于冷却飞机启动器/发电机
公开(公告)号：US07883053B2
公开(公告)日：2011-02-08
申请号：US12244595
申请日：2008-10-02
申请人： Edward Zielinski , Thomas M. Murray
发明人： Edward Zielinski , Thomas M. Murray
IPC分类号： B64D33/10
CPC分类号： F28D7/0066 , B64D13/00 , F28D1/0435 , F28D7/0083 , F28D2021/0021 , Y02T50/44 , Y02T50/56
摘要： Heat exchanger systems and associated systems and methods for cooling aircraft starters/generators are disclosed. A system in accordance with one embodiment includes a first fluid flow path for a first fluid, a second fluid flow path for a second fluid, and a third fluid flow path for a third fluid. The first and second flow paths are positioned proximate to the third flow path to transfer heat between the third fluid and both the first and second fluids. The third flow path is configured to allow a transfer of heat between the second and third fluids at a first transfer rate when the first fluid carries heat at a first rate, and at a second transfer rate different than the first transfer rate when the first fluid does not carry heat, or carries heat at a second rate less than the first rate. Accordingly, when the heat to be rejected by one fluid is decreased, the heat transfer rate for the remaining fluid can be increased.
摘要翻译：公开了用于冷却飞机起动器/发电机的热交换器系统和相关系统和方法。根据一个实施例的系统包括用于第一流体的第一流体流动路径，用于第二流体的第二流体流动路径和用于第三流体的第三流体流动路径。第一和第二流动路径定位成靠近第三流动路径，以在第三流体和第一和第二流体两者之间传递热量。第三流动路径被配置为当第一流体以第一速率承载热量时以第一流体的速率传递第二流体和第三流体之间的热量，并且当第一流体不携带热量，或以低于第一速率的第二速率承载热量。因此，当由一种流体排出的热量降低时，可以增加剩余流体的传热速率。

5. 发明申请

US20090025913A1 Heat Exchanger Systems and Associated Systems and Methods for Cooling Aircraft Starter/Generators 有权
标题翻译：热交换器系统及相关系统和方法用于冷却飞机启动器/发电机
公开(公告)号：US20090025913A1
公开(公告)日：2009-01-29
申请号：US12244595
申请日：2008-10-02
申请人： Edward Zielinski , Thomas M. Murray
发明人： Edward Zielinski , Thomas M. Murray
IPC分类号： F28D7/10
CPC分类号： F28D7/0066 , B64D13/00 , F28D1/0435 , F28D7/0083 , F28D2021/0021 , Y02T50/44 , Y02T50/56
摘要： Heat exchanger systems and associated systems and methods for cooling aircraft starters/generators are disclosed. A system in accordance with one embodiment includes a first fluid flow path for a first fluid, a second fluid flow path for a second fluid, and a third fluid flow path for a third fluid. The first and second flow paths are positioned proximate to the third flow path to transfer heat between the third fluid and both the first and second fluids. The third flow path is configured to allow a transfer of heat between the second and third fluids at a first transfer rate when the first fluid carries heat at a first rate, and at a second transfer rate different than the first transfer rate when the first fluid does not carry heat, or carries heat at a second rate less than the first rate. Accordingly, when the heat to be rejected by one fluid is decreased, the heat transfer rate for the remaining fluid can be increased.
摘要翻译：公开了用于冷却飞机起动器/发电机的热交换器系统和相关系统和方法。根据一个实施例的系统包括用于第一流体的第一流体流动路径，用于第二流体的第二流体流动路径和用于第三流体的第三流体流动路径。第一和第二流动路径靠近第三流动路径定位，以在第三流体和第一和第二流体两者之间传递热量。第三流动路径被配置为当第一流体以第一速率承载热量时以第一流体的速率传递第二流体和第三流体之间的热量，并且当第一流体不携带热量，或以低于第一速率的第二速率承载热量。因此，当由一种流体排出的热量降低时，可以增加剩余流体的传热速率。

6. 发明授权

US07207521B2 Electric-based secondary power system architectures for aircraft 有权
公开(公告)号：US07207521B2
公开(公告)日：2007-04-24
申请号：US11301179
申请日：2005-12-12
申请人： Warren A. Atkey , Alan T. Bernier , Michael D. Bowman , Thomas A. Campbell , Jonathan M. Cruse , Charles J. Fiterman , Charles S. Meis , Casey Y. K. Ng , Farhad Nozari , Edward Zielinski
发明人： Warren A. Atkey , Alan T. Bernier , Michael D. Bowman , Thomas A. Campbell , Jonathan M. Cruse , Charles J. Fiterman , Charles S. Meis , Casey Y. K. Ng , Farhad Nozari , Edward Zielinski
IPC分类号： B64D41/00
CPC分类号： B64D13/08 , B64D13/06 , B64D41/00 , B64D2013/0611 , B64D2013/064 , B64D2013/0644 , B64D2041/005 , B64D2221/00 , Y02T50/44 , Y02T50/53 , Y02T50/56 , Y02T90/36
摘要： Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet engine. The jet engine can be configured to provide propulsive thrust to the aircraft, and the electric generator can be configured to receive shaft power from the jet engine. The environmental control system can be configured to provide outside air to a passenger cabin of the aircraft in the absence of bleed air from the jet engine.

7. 发明授权

US08986816B2 Decorative decal system for an aircraft 有权
标题翻译：飞机装饰贴花系统
公开(公告)号：US08986816B2
公开(公告)日：2015-03-24
申请号：US13180988
申请日：2011-07-12
申请人： Edward Zielinski , James T. Iwamoto
发明人： Edward Zielinski , James T. Iwamoto
IPC分类号： B32B3/00 , B64D45/02 , B32B3/10 , B32B5/02 , B32B15/02 , B32B15/20 , B32B27/06
CPC分类号： B64D45/02 , B32B3/10 , B32B5/02 , B32B5/028 , B32B15/02 , B32B15/20 , B32B27/06 , B32B2262/103 , B32B2405/00 , B32B2451/00 , B32B2605/18 , Y10T428/24802 , Y10T428/24851 , Y10T428/24917
摘要： A method and apparatus comprising a layer of material having a decorative graphic and an electrically conductive material in the layer of material. The layer of material is configured to be attached to a surface of an aircraft. The electrically conductive material is configured to cause a current from an atmospheric electrostatic discharge contacting the layer of material to spread out in a desired amount within the layer of material.
摘要翻译：一种包括在该材料层中具有装饰图形和导电材料的材料层的方法和装置。材料层被配置成附接到飞行器的表面。导电材料被配置成使来自与材料层接触的大气静电放电的电流以期望的量在材料层内展开。

8. 发明授权

US08464740B2 Combustor fuel control systems with flow divider assemblies 有权
标题翻译：具有分流器组件的燃烧器燃料控制系统
公开(公告)号：US08464740B2
公开(公告)日：2013-06-18
申请号：US13159175
申请日：2011-06-13
申请人： Edward Zielinski
发明人： Edward Zielinski
IPC分类号： G05D11/03 , F02C9/26
CPC分类号： F23K5/06 , F02C7/228 , F23K5/14 , F23K5/147 , F23K2900/05001 , F23K2900/05141 , F23N1/00 , Y10T137/0318 , Y10T137/0363 , Y10T137/2521 , Y10T137/2524 , Y10T137/2559
摘要： A flow divider assembly includes a dividing valve and a balancing valve. The dividing valve includes a dividing cavity configured to receive a flow of fuel and a piston device arranged within the dividing cavity and selectively positioned to divide the flow of fuel in the dividing cavity into the first dividing valve port and the second dividing valve port. The balancing valve is fluidly coupled to the dividing valve and configured to receive the first portion and the second portion of the flow. The balancing valve includes a balancing cavity and a balancing device arranged within the balancing cavity and selectively positioned to direct the first portion of the flow into the first balancing cavity port at a third pressure and the second portion of the flow into the second balancing cavity port at a fourth pressure such that the first pressure is approximately equal to the second pressure.
摘要翻译：分流器组件包括分隔阀和平衡阀。分隔阀包括：分配腔，其构造成容纳燃料流;以及活塞装置，其布置在分隔腔内，并且选择性地定位成将分隔腔中的燃料流分成第一分隔阀口和第二分隔阀口。平衡阀流体地联接到分隔阀并且构造成接收流动的第一部分和第二部分。所述平衡阀包括平衡腔和平衡装置，所述平衡腔和所述平衡装置布置在所述平衡腔内并且被选择性地定位成将所述第一部分的流以第三压力引导到所述第一平衡腔端口中，并且所述流体的第二部分进入所述第二平衡腔口在第四压力下使得第一压力近似等于第二压力。

9. 发明申请

US20060168968A1 Systems and methods for starting aircraft engines 有权
公开(公告)号：US20060168968A1
公开(公告)日：2006-08-03
申请号：US11051272
申请日：2005-02-03
申请人： Edward Zielinski , Alan Bernier , Kent Knechtel , Thomas Campbell , Jeffrey White , Mark Ralston
发明人： Edward Zielinski , Alan Bernier , Kent Knechtel , Thomas Campbell , Jeffrey White , Mark Ralston
IPC分类号： F02C7/26
CPC分类号： F02C7/262 , F02C7/268 , F02C7/275 , F02C7/277 , F05D2220/76 , F05D2220/764 , Y02T50/671
摘要： Methods and systems for starting aircraft turbofan engines are disclosed. A system in accordance with one embodiment includes an electrically-powered starter motor coupled to a turbofan engine to provide power to the turbofan engine during an engine start procedure. The system can further include an on-board, deployable, ram air driven turbine coupled to an electrical generator, which is in turn coupled to the starter motor to provide electrical power to the starter motor. In other embodiments, the ram air driven turbine can be replaced with a fuel cell or a battery. In still further embodiments, a single controller can control operation of both the engine starter and other motors of the aircraft.

10. 发明申请

US20120312378A1 COMBUSTOR FUEL CONTROL SYSTEMS WITH FLOW DIVIDER ASSEMBLIES 有权
标题翻译：燃烧器燃油控制系统与流动分流器组件
公开(公告)号：US20120312378A1
公开(公告)日：2012-12-13
申请号：US13159175
申请日：2011-06-13
申请人： Edward Zielinski
发明人： Edward Zielinski
IPC分类号： F15D1/00
CPC分类号： F23K5/06 , F02C7/228 , F23K5/14 , F23K5/147 , F23K2900/05001 , F23K2900/05141 , F23N1/00 , Y10T137/0318 , Y10T137/0363 , Y10T137/2521 , Y10T137/2524 , Y10T137/2559
摘要： A flow divider assembly includes a dividing valve and a balancing valve. The dividing valve includes a dividing cavity configured to receive a flow of fuel and a piston device arranged within the dividing cavity and selectively positioned to divide the flow of fuel in the dividing cavity into the first dividing valve port and the second dividing valve port. The balancing valve is fluidly coupled to the dividing valve and configured to receive the first portion and the second portion of the flow. The balancing valve includes a balancing cavity and a balancing device arranged within the balancing cavity and selectively positioned to direct the first portion of the flow into the first balancing cavity port at a third pressure and the second portion of the flow into the second balancing cavity port at a fourth pressure such that the first pressure is approximately equal to the second pressure.
摘要翻译：分流器组件包括分隔阀和平衡阀。分隔阀包括：分配腔，其构造成容纳燃料流;以及活塞装置，其布置在分隔腔内，并且选择性地定位成将分隔腔中的燃料流分成第一分隔阀口和第二分隔阀口。平衡阀流体地联接到分隔阀并且构造成接收流动的第一部分和第二部分。所述平衡阀包括平衡腔和平衡装置，所述平衡腔和所述平衡装置布置在所述平衡腔内并且被选择性地定位成将所述第一部分的流以第三压力引导到所述第一平衡腔端口中，并且所述流体的第二部分进入所述第二平衡腔口在第四压力下使得第一压力近似等于第二压力。

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