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1. 发明公开

EP2402251A2 A jet engine installation 无效转让
标题翻译： Triebwerkeinbau
公开(公告)号：EP2402251A2
公开(公告)日：2012-01-04
申请号：EP11171651.0
申请日：2011-06-28
申请人： Rolls-Royce plc
发明人： Morvant, Romuald , Britchford, Kevin Mark
IPC分类号： B64D29/02
CPC分类号： B64D29/02 , B64C23/06 , Y02T50/162
摘要： Noise generated by a gas turbine engine 6 supported by a pylon 8 on a wing 2 of an aircraft is reduced by influencing a shear layer generated between the free-stream flowfield and flow from the engine 6. The shear layer is influenced by means of one or more winglets 18, 20, 22 which interact with the free-stream flowfield to deflect the shear layer 14 downwardly, to avoid interaction with a flap 4 on the wing 2, or to reduce the strength of the shear layer 14.
摘要翻译：由飞机机翼2上的塔架8支撑的燃气涡轮发动机6产生的噪声通过影响在自由流动流场和来自发动机6的流量之间产生的剪切层而减小。剪切层受到一个或更多的小翼18,20,22，其与自由流动流场相互作用以向下偏转剪切层14，以避免与机翼2上的翼片4相互作用，或降低剪切层14的强度。

2. 发明公开

EP2402250A3 Pylon for attaching a gas turbine engine 失效转让
标题翻译： ast ur ur ung ung。。。。。。。。。
公开(公告)号：EP2402250A3
公开(公告)日：2015-11-04
申请号：EP11170181.9
申请日：2011-06-16
申请人： Rolls-Royce plc
发明人： Morvant, Romuald , Britchford, Kevin Mark
IPC分类号： B64D29/02 , B64C7/02 , B64D33/04
CPC分类号： B64D29/02 , B64C7/02 , B64D33/04
摘要： A pylon (5a) is provided for attachment of a gas turbine engine (1) to a wing of an aircraft. The gas turbine engine (1) comprises a core fairing (3) surrounding a core generator and defining a nozzle for discharging a core gas flow, and a fan nacelle (2) surrounding the core fairing (3) to define an annular bypass duct (4) therebetween for discharging fan air. The pylon (5a) has a trailing edge (7) which is rearward of the trailing edge of the core fairing (3) and the trailing edge of the fan nacelle (2). The pylon (5a) further has having two laterally-spaced side faces which span the bypass duct between the fan nacelle (2) and the core fairing (3) and extend in the rearward direction of the engine to end at the trailing edge (7) of the pylon (5a). Each side face has a bottom edge which extends in a rearward direction of the engine (1) from the core fairing (3) to the bottom end of the trailing edge of the pylon. The bottom edges merge at a merging position between the trailing edge of the fan nacelle (2) and the trailing edge (7) of the pylon (5a) such that the bottom edges form a single bottom edge from the merging position to the bottom end of the trailing edge (7) of the pylon (5a). The pylon (5a) is intended to exert control on the bypass flow of a gas turbine engine. Other pylons are also provided which can also exert such control.
摘要翻译：提供了一种用于将燃气涡轮发动机（1）附接到飞机机翼的塔（5a）。燃气涡轮发动机（1）包括围绕芯发生器并且限定用于排出芯气流的喷嘴的芯整流罩（3）和围绕芯整流罩（3）的风扇机舱（2），以限定环形旁路管道 4），用于排出风扇空气。塔架（5a）具有后缘（7），该后缘位于芯整流罩（3）的后缘和风扇机舱（2）的后缘的后方。塔架（5a）还具有两个横向间隔开的侧面，该侧面跨越风扇机舱（2）和芯整流装置（3）之间的旁路管道，并且在发动机的向后方向上延伸以在后缘（7 ）的塔（5a）。每个侧面具有沿着发动机（1）的向后方向从芯整流罩（3）延伸到塔架的后缘的底端的底边缘。底部边缘在风扇机舱（2）的后缘和塔架（5a）的后缘（7）之间的合并位置处合并，使得底部边缘从合并位置到底部端部形成单个底部边缘的塔架（5a）的后缘（7）。塔（5a）旨在对燃气涡轮发动机的旁路流进行控制。还提供了还可以施加这种控制的其它塔架。

3. 发明公开

EP2402251A3 A jet engine installation 无效转让
标题翻译：动力装置的安装
公开(公告)号：EP2402251A3
公开(公告)日：2015-08-05
申请号：EP11171651.0
申请日：2011-06-28
申请人： Rolls-Royce plc
发明人： Morvant, Romuald , Britchford, Kevin Mark
IPC分类号： B64D29/02 , B64C23/06
CPC分类号： B64D29/02 , B64C23/06 , Y02T50/162
摘要： Noise generated by a gas turbine engine 6 supported by a pylon 8 on a wing 2 of an aircraft is reduced by influencing a shear layer generated between the free-stream flowfield and flow from the engine 6. The shear layer is influenced by means of one or more winglets 18, 20, 22 which interact with the free-stream flowfield to deflect the shear layer 14 downwardly, to avoid interaction with a flap 4 on the wing 2, or to reduce the strength of the shear layer 14.

4. 发明公开

EP2402250A2 Pylon for attaching a gas turbine engine 失效转让
标题翻译：桅杆用于发动机的附连
公开(公告)号：EP2402250A2
公开(公告)日：2012-01-04
申请号：EP11170181.9
申请日：2011-06-16
申请人： Rolls-Royce plc
发明人： Morvant, Romuald , Britchford, Kevin Mark
IPC分类号： B64D29/02
CPC分类号： B64D29/02 , B64C7/02 , B64D33/04
摘要： A pylon (5a) is provided for attachment of a gas turbine engine (1) to a wing of an aircraft. The gas turbine engine (1) comprises a core fairing (3) surrounding a core generator and defining a nozzle for discharging a core gas flow, and a fan nacelle (2) surrounding the core fairing (3) to define an annular bypass duct (4) therebetween for discharging fan air. The pylon (5a) has a trailing edge (7) which is rearward of the trailing edge of the core fairing (3) and the trailing edge of the fan nacelle (2). The pylon (5a) further has having two laterally-spaced side faces which span the bypass duct between the fan nacelle (2) and the core fairing (3) and extend in the rearward direction of the engine to end at the trailing edge (7) of the pylon (5a). Each side face has a bottom edge which extends in a rearward direction of the engine (1) from the core fairing (3) to the bottom end of the trailing edge of the pylon. The bottom edges merge at a merging position between the trailing edge of the fan nacelle (2) and the trailing edge (7) of the pylon (5a) such that the bottom edges form a single bottom edge from the merging position to the bottom end of the trailing edge (7) of the pylon (5a). The pylon (5a) is intended to exert control on the bypass flow of a gas turbine engine. Other pylons are also provided which can also exert such control.

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