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1.发明申请Turbojet designed to be fixed onto the AFT part of the fuselage of an aircraft, in upper position 有权Turbojet旨在固定在飞机机身的AFT部分，位于上位公开(公告)号：US20050178887A1
公开(公告)日：2005-08-18
申请号：US10986004
申请日：2004-11-12
申请人： Bruno Beutin , Didier Yvon , Georges Mazeaud , Fabien Burdin
发明人： Bruno Beutin , Didier Yvon , Georges Mazeaud , Fabien Burdin
摘要： The turbojet according to the invention is designed to be fixed onto the upper part of the aft section of the fuselage of an aircraft using at least one coat hanger, the turbojet comprising a fan, a forward casing, an aft casing, accessories arranged around the periphery of the forward casing, the forward casing comprising attachment points, for the coat hanger. The attachment points are arranged so that the turbojet can be installed indifferently on either side of the aircraft fuselage, accessories being arranged on the casing so that they are accessible from the outside of the fuselage regardless of which side the installation is done.
摘要翻译： 根据本发明的涡轮喷气发动机被设计成使用至少一个衣架固定到飞行器机身的后部的上部，涡轮喷气发动机包括风扇，前壳，后壳，围绕 前壳体的周边，前部壳体包括用于衣架的附接点。 附接点被布置成使得涡轮喷气发动机可以无差别地安装在飞行器机身的任一侧上，附件被布置在壳体上，使得它们可以从机身的外部接近，而不管安装的哪一方。
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2.发明授权Turbojet designed to be fixed onto the AFT part of the fuselage of an aircraft, in upper position 有权Turbojet旨在固定在飞机机身的AFT部分，位于上位公开(公告)号：US07007890B2
公开(公告)日：2006-03-07
申请号：US10986004
申请日：2004-11-12
申请人： Bruno Beutin , Didier Yvon , Georges Mazeaud , Fabien Burdin
发明人： Bruno Beutin , Didier Yvon , Georges Mazeaud , Fabien Burdin
IPC分类号： B64D27/00
摘要： The turbojet according to the invention is designed to be fixed onto the upper part of the aft section of the fuselage of an aircraft using at least one coat hanger, the turbojet comprising a fan, a forward casing, an aft casing, accessories arranged around the periphery of the forward casing, the forward casing comprising attachment points, for the coat hanger. The attachment points are arranged so that the turbojet can be installed indifferently on either side of the aircraft fuselage, accessories being arranged on the casing so that they are accessible from the outside of the fuselage regardless of which side the installation is done.
摘要翻译： 根据本发明的涡轮喷气发动机被设计成使用至少一个衣架固定到飞行器机身的后部的上部，涡轮喷气发动机包括风扇，前壳，后壳，围绕 前壳体的周边，前部壳体包括用于衣架的附接点。 附接点被布置成使得涡轮喷气发动机可以无差别地安装在飞行器机身的任一侧上，附件被布置在壳体上，使得它们可以从机身的外部接近，而不管安装的哪一方。
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3.发明申请Cooling system for hot parts of an aircraft engine, and aircraft engine equipped with such a cooling system 审中-公开用于飞机发动机热部件的冷却系统，以及配备这种冷却系统的飞机发动机公开(公告)号：US20050150970A1
公开(公告)日：2005-07-14
申请号：US11006635
申请日：2004-12-08
CPC分类号： F02K3/02 , F02C7/141 , F05D2260/208 , F28D21/0014 , F28D2021/0021 , Y02T50/671 , Y02T50/676
摘要： The cooling system (30) for an aircraft engine (10) comprises a channel (32) that draws off cold air in the secondary air flow (200), and a heat exchanger (34) located in the channel (32) and in which hot air circulates. The channel (32) comprises: a supply pipe (322) and an evacuation pipe (326) fixed to the nacelle (324), an intermediate box (324) located between the supply pipe (322) and the evacuation pipe (326), fixed to the engine (10), and in which the heat exchanger (34) is placed. Application to cooling of hot parts (22) in an aircraft engine (10).
摘要翻译： 用于飞机发动机（10）的冷却系统（30）包括抽出二次空气流（200）中的冷空气的通道（32）和位于通道（32）中的热交换器（34），其中 热空气循环。 通道（32）包括：供给管（322）和固定在机舱（324）上的排气管326，位于供给管322和排气管326之间的中间箱324， 固定在发动机（10）上，其中放置有热交换器（34）。 适用于飞机发动机（10）中的热部件（22）的冷却。
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公开(公告)号：US20070084216A1
公开(公告)日：2007-04-19
申请号：US11427151
申请日：2006-06-28
申请人： Georges MAZEAUD , Didier Yvon
发明人： Georges MAZEAUD , Didier Yvon
IPC分类号： F02C7/32
摘要： A device for supporting and housing auxiliaries in a bypass turbojet, comprising two coaxial case rings arranged one inside the other and connected by tubular radial arms through which fluid ducts and electric cables pass, at least one of the radial arms comprising on a lateral face a detachable panel whose removal allows access to turbojet equipment situated radially inside the internal case ring in alignment with the radial arm.
摘要翻译： 一种用于在旁路涡轮喷气发动机中支撑和容纳辅助设备的装置，包括两个同轴的壳环，所述两个同轴壳环以另一个内部布置并通过管状径向臂连接，流体管道和电缆通过该径向臂，至少一个径向臂包括在侧面上 可拆卸的面板，其移除允许进入位于内部环形圈径向内侧的与径向臂对准的涡轮喷气发动机设备。
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