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1. 发明授权

US08083467B2 Apparatus and method for controlling a rotary machine using pressurized gas 有权
标题翻译：使用加压气体控制旋转机器的装置和方法
公开(公告)号：US08083467B2
公开(公告)日：2011-12-27
申请号：US11779147
申请日：2007-07-17
申请人： Karl Edward Sheldon , Michael Anthony Shockling
发明人： Karl Edward Sheldon , Michael Anthony Shockling
IPC分类号： F01D21/02
CPC分类号： F02C6/08 , F01D21/006 , F01D21/02
摘要： An apparatus and method for controlling rotating bladed machinery by using a source of pressurized gas is disclosed. The source of pressurized gas, such as air, imparts braking torque on a turbomachinery component through the use of one or more impinging orifices or jets. The orientation of the jets is such that the transfer of momentum from the pressurized gas results in a force substantially opposite the direction of rotation of the turbomachinery component. This transfer of momentum from the pressurized gas allows for a controlling torque to be applied to the turbomachinery component without the need of mechanical and/or electrical devices applying torque to the rotating shaft.
摘要翻译：公开了一种通过使用加压气体源来控制旋转叶片机械的装置和方法。诸如空气的加压气体源通过使用一个或多个冲击孔或喷嘴将制动扭矩赋予涡轮机械部件。射流的方向是这样的：从加压气体传递动量导致基本上与涡轮机械部件的旋转方向相反的力。来自加压气体的动量传递允许将控制扭矩施加到涡轮机械部件，而不需要向旋转轴施加扭矩的机械和/或电气装置。

2. 发明授权

US07707838B2 Auxiliary power unit assembly 有权
标题翻译：辅助动力装置总成
公开(公告)号：US07707838B2
公开(公告)日：2010-05-04
申请号：US11590114
申请日：2006-10-31
申请人： Karl Edward Sheldon , Charles Erklin Seeley , Ludwig Christian Haber
发明人： Karl Edward Sheldon , Charles Erklin Seeley , Ludwig Christian Haber
IPC分类号： F02C6/04
CPC分类号： B64D33/02 , B64D41/00 , B64D2033/0206 , B64D2033/0213 , B64D2041/002 , F02C7/32 , F02C9/16 , F05D2220/50 , F05D2220/76 , F05D2270/101 , Y02T50/672
摘要： An embodiment of the technology described herein is an auxiliary power unit assembly. The auxiliary power unit assembly includes an auxiliary power unit being installable in an aircraft having a cabin, a duct connecting the cabin and the auxiliary power unit, and an airflow management feature in the duct.
摘要翻译：本文描述的技术的实施例是辅助动力单元组件。辅助动力单元组件包括可安装在具有舱室的飞机中的辅助动力单元，连接舱室和辅助动力单元的管道以及管道中的气流管理特征。

3. 发明申请

US20080098747A1 Auxiliary power unit assembly 有权
标题翻译：辅助动力装置总成
公开(公告)号：US20080098747A1
公开(公告)日：2008-05-01
申请号：US11590114
申请日：2006-10-31
申请人： Karl Edward Sheldon , Charles Erklin Seeley , Ludwig Christian Haber
发明人： Karl Edward Sheldon , Charles Erklin Seeley , Ludwig Christian Haber
IPC分类号： F02C6/00
CPC分类号： B64D33/02 , B64D41/00 , B64D2033/0206 , B64D2033/0213 , B64D2041/002 , F02C7/32 , F02C9/16 , F05D2220/50 , F05D2220/76 , F05D2270/101 , Y02T50/672
摘要： An embodiment of the technology described herein is an auxiliary power unit assembly. The auxiliary power unit assembly includes an auxiliary power unit being installable in an aircraft having a cabin, a duct connecting the cabin and the auxiliary power unit, and an airflow management feature in the duct.
摘要翻译：本文描述的技术的实施例是辅助动力单元组件。辅助动力单元组件包括可安装在具有舱室的飞机中的辅助动力单元，连接舱室和辅助动力单元的管道以及管道中的气流管理特征。

4. 发明申请

US20120119518A1 AUXILIARY GAS TURBINE ENGINE ASSEMBLY, AIRCRAFT COMPONENT AND CONTROLLER 审中-公开
标题翻译：辅助气体涡轮发动机总成，飞机组件和控制器
公开(公告)号：US20120119518A1
公开(公告)日：2012-05-17
申请号：US13339552
申请日：2011-12-29
申请人： Michael SHOCKLING , Karl Edward Sheldon
发明人： Michael SHOCKLING , Karl Edward Sheldon
IPC分类号： H02P9/04 , F02C6/08
CPC分类号： F02C3/22 , F02C6/04 , F02C6/08
摘要： A non-aircraft-propelling auxiliary gas turbine engine assembly includes an auxiliary gas turbine engine and a mixing damper. The auxiliary engine and the mixing damper are installable in an aircraft having at least one aircraft-propelling main gas turbine engine. The auxiliary engine includes a compressor having a compressor inlet. The mixing damper has first and second inlets and has an outlet. The outlet is fluidly connectable to the compressor inlet. The first and second inlets are adapted to receive first and second gas streams which have been compressed by at least one main engine. An aircraft component includes a mixing damper. A controller includes a program which instructs the controller to increase/decrease a first gas stream in response to increasing/decreasing electrical demands on an electric generator operatively connected to an auxiliary gas turbine engine of an aircraft.
摘要翻译：非飞机推进辅助燃气涡轮发动机组件包括辅助燃气涡轮发动机和混合阻尼器。辅助发动机和混合阻尼器可安装在具有至少一个飞机推进主燃气涡轮发动机的飞行器中。辅助发动机包括具有压缩机入口的压缩机。混合阻尼器具有第一和第二入口并具有出口。出口可流体地连接到压缩机入口。第一和第二入口适于接受已被至少一个主发动机压缩的第一和第二气流。飞机部件包括混合阻尼器。控制器包括指示控制器响应于对与飞机的辅助燃气涡轮发动机连接的发电机的电力需求的增加/减少而增加/减少第一气流的程序。

5. 发明授权

US07721554B2 Aircraft auxiliary gas turbine engine and method for operating 有权
标题翻译：飞机辅助燃气轮机及其操作方法
公开(公告)号：US07721554B2
公开(公告)日：2010-05-25
申请号：US11345950
申请日：2006-02-02
申请人： Chellappa Balan , Karl Edward Sheldon
发明人： Chellappa Balan , Karl Edward Sheldon
IPC分类号： F02C6/04
CPC分类号： B64D41/00 , B64D2013/0611 , B64D2041/002 , F02C7/32 , F05D2220/50
摘要： A non-aircraft-propelling auxiliary gas turbine engine installable in an aircraft having a cabin adapted to be pressurized. The auxiliary gas turbine engine includes an auxiliary-gas-turbine-engine compressor having an inlet, wherein the inlet is adapted to receive pressurized air from the cabin. A method for operating a non-aircraft-propelling auxiliary gas turbine engine of an aircraft includes providing pressurized air from the cabin of the aircraft to an inlet of a compressor of the auxiliary gas turbine engine. The method includes providing compressed air from the compressor to a combustor of the auxiliary gas turbine engine and includes providing combustion gases from the combustor to a turbine of the auxiliary gas turbine engine, wherein the turbine is mechanically coupled to the compressor.
摘要翻译：可安装在具有适于加压的舱室的飞行器中的非飞机推进辅助燃气涡轮发动机。辅助燃气涡轮发动机包括具有入口的辅助燃气涡轮发动机压缩机，其中入口适于从舱室接收加压空气。用于操作飞行器的非飞机推进辅助燃气涡轮发动机的方法包括将来自飞机的舱室的加压空气提供给辅助燃气涡轮发动机的压缩机的入口。该方法包括将压缩空气从压缩机提供给辅助燃气涡轮发动机的燃烧器，并且包括将来自燃烧器的燃烧气体提供给辅助燃气涡轮发动机的涡轮机，其中涡轮机械地联接到压缩机。

6. 发明申请

US20100028126A1 APPARATUS AND METHOD FOR CONTROLLING A ROTARY MACHINE USING PRESSURIZED GAS 有权
标题翻译：使用加压气体控制旋转机的装置和方法
公开(公告)号：US20100028126A1
公开(公告)日：2010-02-04
申请号：US11779147
申请日：2007-07-17
申请人： Karl Edward Sheldon , Michael Anthony Shockling
发明人： Karl Edward Sheldon , Michael Anthony Shockling
IPC分类号： F01D17/06
CPC分类号： F02C6/08 , F01D21/006 , F01D21/02
摘要： An apparatus and method for controlling rotating bladed machinery by using a source of pressurized gas is disclosed. The source of pressurized gas, such as air, imparts braking torque on a turbomachinery component through the use of one or more impinging orifices or jets. The orientation of the jets is such that the transfer of momentum from the pressurized gas results in a force substantially opposite the direction of rotation of the turbomachinery component. This transfer of momentum from the pressurized gas allows for a controlling torque to be applied to the turbomachinery component without the need of mechanical and/or electrical devices applying torque to the rotating shaft.
摘要翻译：公开了一种通过使用加压气体源来控制旋转叶片机械的装置和方法。诸如空气的加压气体源通过使用一个或多个冲击孔或喷嘴将制动扭矩赋予涡轮机械部件。射流的方向是这样的：从加压气体传递动量导致基本上与涡轮机械部件的旋转方向相反的力。来自加压气体的动量传递允许将控制扭矩施加到涡轮机械部件，而不需要向旋转轴施加扭矩的机械和/或电气装置。

7. 发明授权

US07673459B2 System and method for providing air to a compressor of an aircraft auxiliary gas turbine engine 有权
标题翻译：用于向飞机辅助燃气涡轮发动机的压缩机提供空气的系统和方法
公开(公告)号：US07673459B2
公开(公告)日：2010-03-09
申请号：US11398108
申请日：2006-04-05
申请人： Karl Edward Sheldon , John Turco
发明人： Karl Edward Sheldon , John Turco
IPC分类号： F02C6/06 , F02C7/00
CPC分类号： B64D41/00 , B64D2033/0213 , F01D13/02 , F05D2220/50 , Y10S62/05
摘要： A system for providing air to a compressor of an auxiliary gas turbine engine of an aircraft. A system turbine has an inlet adapted to receive compressed air from the aircraft. A system compressor is mechanically coupled to the system turbine and has an inlet adapted to receive atmospheric air. The outlets of the system turbine and the system compressor are fluidly connectable to the inlet of the compressor of the auxiliary gas turbine engine. A method includes providing compressed air from an aircraft to an inlet of a system turbine mechanically coupled to a system compressor. The method includes providing atmospheric air to an inlet of the system compressor. The method includes providing the inlet of the compressor of an auxiliary gas turbine engine with air from an outlet of the system turbine and with air from an outlet of the system compressor.
摘要翻译：一种用于向飞行器的辅助燃气涡轮发动机的压缩机提供空气的系统。系统涡轮机具有适于接收来自飞行器的压缩空气的入口。系统压缩机机械耦合到系统涡轮机并且具有适于接收空气的入口。系统涡轮机和系统压缩机的出口可流体地连接到辅助燃气涡轮发动机的压缩机的入口。一种方法包括将来自飞行器的压缩空气提供给机械耦合到系统压缩机的系统涡轮机的入口。该方法包括向系统压缩机的入口提供大气。该方法包括向辅助燃气涡轮发动机的压缩机的入口提供来自系统涡轮机的出口的空气和来自系统压缩机的出口的空气。

8. 发明申请

US20090025393A1 Auxiliary power unit assembly 审中-公开
标题翻译：辅助动力装置总成
公开(公告)号：US20090025393A1
公开(公告)日：2009-01-29
申请号：US11590041
申请日：2006-10-31
申请人： Karl Edward Sheldon , Charles Erklin Seeley , Ludwig Christian Haber , Trevor Howard Wood , Jonathan Glenn Luedke , Chingwei Michael Shieh
发明人： Karl Edward Sheldon , Charles Erklin Seeley , Ludwig Christian Haber , Trevor Howard Wood , Jonathan Glenn Luedke , Chingwei Michael Shieh
IPC分类号： F02C7/24 , F02K1/06 , F01N1/24
CPC分类号： B64D33/02 , B64D41/00 , B64D2033/0206 , B64D2033/0213 , B64D2041/002 , F02C7/045 , F02C7/32 , F05D2220/50 , F05D2260/962 , F05D2270/101 , Y02T50/672
摘要： An embodiment of the technology described herein is an auxiliary power unit assembly. The auxiliary power unit assembly includes an auxiliary power unit being installable in an aircraft having a cabin, a duct connecting the cabin and the auxiliary power unit, and a noise reduction feature in the duct.
摘要翻译：本文描述的技术的实施例是辅助动力单元组件。辅助动力单元组件包括可安装在具有舱室的飞行器中的辅助动力单元，连接舱室和辅助动力单元的管道以及管道中的降噪特征。

9. 发明授权

US06815102B2 Energy management system for a rotary machine and method therefor 有权
标题翻译：旋转机械能量管理系统及其方法
公开(公告)号：US06815102B2
公开(公告)日：2004-11-09
申请号：US10064134
申请日：2002-06-13
申请人： Michael John Bowman , Gautam (NMN) Sinha , Karl Edward Sheldon
发明人： Michael John Bowman , Gautam (NMN) Sinha , Karl Edward Sheldon
IPC分类号： H01M804
CPC分类号： H01M8/04014 , F05B2220/702 , F05B2220/704 , F05B2270/304 , F05D2250/82 , H01M8/04111 , H01M2250/407 , Y02E60/563
摘要： In energy management system is provided for a power generating device having a working fluid intake in which the energy management system comprises an electrical dissipation device coupled to the power generating device and a dissipation device cooling system configured to direct a portion of a working fluid to the electrical dissipation device so as to provide thermal control to the electrical dissipation device.

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