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1. 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。

2. 发明申请

US20070220900A1 Auxiliary gas turbine engine assembly, aircraft component and controller 审中-公开
标题翻译：辅助燃气轮机发动机总成，飞机部件和控制器
公开(公告)号：US20070220900A1
公开(公告)日：2007-09-27
申请号：US11389711
申请日：2006-03-27
申请人： Michael Shockling , Karl Sheldon
发明人： Michael Shockling , Karl Sheldon
IPC分类号： F02C6/00
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。

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