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1. 发明公开

EP1990517A3 Power generation system for an aircraft 有权转让
标题翻译：飞机的发电系统
公开(公告)号：EP1990517A3
公开(公告)日：2010-12-22
申请号：EP08251656.8
申请日：2008-05-09
申请人： United Technologies Corporation
发明人： Schwarz, Frederick M. , Fentress, Brian M. , Berrymann, Andrew P. , Glahn, Jorn A. , Lents, Charles E.
IPC分类号： F02C6/08
CPC分类号： F02C5/06 , F02C6/06 , F02C6/08 , F02C7/32 , F05D2220/50 , F05D2220/76 , F05D2260/85
摘要： A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine (14) in an engine compartment in the aircraft with an air inlet duct (11) in the aircraft that is curved along its extent in leading to an air compressor (23) in the gas turbine engine having a compressor air transfer duct (30) extending therefrom to an internal combustion engine (34) provided as an intermittent combustion engine at an air intake thereof. An inlet duct manifold (70) is positioned against the duct wall of the inlet duct (11) to cover a perforated portion thereof on the air compressor side of a curve therein with the inlet duct manifold having an inlet air transfer duct (72) extending therefrom that is coupled to the intermittent combustion engine air intake (32).
摘要翻译：一种用于在飞机中推进和产生电力的发电系统，所述发电系统在飞机的发动机舱中具有燃气涡轮发动机（14），所述飞机中具有进气管道（11），所述进气管道沿其领先的程度弯曲连接到燃气涡轮发动机中的空气压缩机（23），该燃气涡轮发动机具有从其延伸到在其空气入口处作为间歇燃烧发动机提供的内燃机（34）的压缩机空气输送管道（30）。入口管道歧管（70）抵靠入口管道（11）的管道壁定位以覆盖其中的曲线的空气压缩机侧上的穿孔部分，其中入口管道歧管具有延伸进入空气传输管道（72）的入口空气传输管道从那里连接到间歇燃烧发动机进气口（32）。

2. 发明公开

EP1990517A2 Power generation system for an aircraft 有权转让
标题翻译： EnergieerzeugungssystemfürFlugzeuge
公开(公告)号：EP1990517A2
公开(公告)日：2008-11-12
申请号：EP08251656.8
申请日：2008-05-09
申请人： United Technologies Corporation
发明人： Schwarz, Frederick M. , Fentress, Brian M. , Berrymann, Andrew P. , Glahn, Jorn A. , Lents, Charles E.
IPC分类号： F02C5/06 , F02C6/06 , F02C6/08 , F02C7/32
CPC分类号： F02C5/06 , F02C6/06 , F02C6/08 , F02C7/32 , F05D2220/50 , F05D2220/76 , F05D2260/85
摘要： A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine (14) in an engine compartment in the aircraft with an air inlet duct (11) in the aircraft that is curved along its extent in leading to an air compressor (23) in the gas turbine engine having a compressor air transfer duct (30) extending therefrom to an internal combustion engine (34) provided as an intermittent combustion engine at an air intake thereof. An inlet duct manifold (70) is positioned against the duct wall of the inlet duct (11) to cover a perforated portion thereof on the air compressor side of a curve therein with the inlet duct manifold having an inlet air transfer duct (72) extending therefrom that is coupled to the intermittent combustion engine air intake (32).
摘要翻译：一种用于在飞行器中推进和产生电力的发电系统，其具有在飞行器中的发动机舱中的燃气涡轮发动机（14），其中在飞机中的空气入口管道（11）沿着其前进方向弯曲涉及一种具有从其延伸到内燃机（34）的压缩机空气输送管道（30）的燃气涡轮发动机中的空气压缩机（23），所述内燃机在其进气口处设置为间歇式内燃机。入口管道歧管（70）抵靠入口管道（11）的管道壁定位以覆盖其曲线的空气压缩机侧上的穿孔部分，入口管道歧管具有延伸的入口空气传送管道（72）从而连接到间歇式内燃机进气口（32）。

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