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1. 发明授权

US08850824B2 Aircraft gas turbine with variable bypass nozzle by deforming element 有权
标题翻译：具有可变旁路喷嘴的飞机燃气轮机通过变形元件
公开(公告)号：US08850824B2
公开(公告)日：2014-10-07
申请号：US13541260
申请日：2012-07-03
申请人： Predrag Todorovic , Miles Trumper
发明人： Predrag Todorovic , Miles Trumper
IPC分类号： F02K1/08 , F02K3/02 , F02K1/82
CPC分类号： F02K1/085 , F02K1/08 , F02K1/827
摘要： The present invention relates to an aircraft gas turbine with a core engine which is surrounded by a bypass duct enclosed radially outwards by a bypass wall, with a radially inner wall of the bypass duct forming with the radially outer bypass wall a bypass nozzle, and with the radially inner wall including an adjusting element extending along the circumference of the inner wall and being deformable radially outwards.
摘要翻译：技术领域本发明涉及一种具有核心发动机的飞机燃气轮机，其由旁路径径向向外封闭的旁通管道围绕，旁路管道的径向内壁与径向外部旁路壁形成旁路喷嘴，并且与所述径向内壁包括沿所述内壁的圆周延伸并且可径向向外变形的调节元件。

2. 发明授权

US08776946B2 Gas turbine exhaust cone 有权
标题翻译：燃气轮机排气锥
公开(公告)号：US08776946B2
公开(公告)日：2014-07-15
申请号：US13980017
申请日：2012-01-19
申请人： Predrag Todorovic
发明人： Predrag Todorovic
IPC分类号： F02K1/82 , F02K1/04 , F02C7/24 , F01D25/30 , F02C5/10 , F02K1/78 , F02K1/00
CPC分类号： F02C7/24 , F01D25/30 , F02C5/10 , F02K1/827 , F05D2260/96
摘要： The present invention relates to a gas-turbine exhaust cone having an outer wall, which is provided with a plurality of recesses, a honeycomb-structured layer, which is arranged on the inside of the outer wall and extends along the inside of the outer wall, an inner wall, which extends substantially parallel to the outer wall and is connected to the honeycomb structure, and at least one annular chamber, which adjoins the inner wall and is centered relative to a central axis, with the inner wall being provided with passage recesses connecting the area of the honeycomb structure to the annular chamber.
摘要翻译：本发明涉及一种具有外壁的燃气轮机排气锥体，其具有多个凹部，蜂窝结构层布置在外壁的内侧并沿着外壁的内侧延伸，内壁，其基本上平行于外壁延伸并连接到蜂窝结构，以及至少一个环形室，其邻接内壁并相对于中心轴线居中，内壁设有通道将蜂窝结构的区域连接到环形室的凹部。

3. 发明授权

US08690098B2 Air ejector nozzle tube for an oil heat exchanger of an aircraft engine 有权
标题翻译：用于飞机发动机的油热交换器的喷射器喷嘴管
公开(公告)号：US08690098B2
公开(公告)日：2014-04-08
申请号：US13039795
申请日：2011-03-03
申请人： Predrag Todorovic
发明人： Predrag Todorovic
IPC分类号： B64D33/10
CPC分类号： B64D27/14 , B64D29/04 , B64D33/10 , B64D2027/005 , B64D2027/026 , Y02T50/66
摘要： An ejector nozzle tube, having along its length an essentially constant, essentially oval hollow cross-section, with a leading edge nozzle, having a rounded exterior cross-section, being arranged at a flow leading-edge area of the ejector nozzle tube. The leading edge nozzle includes a plurality of grooves issuing to the top and bottom sides of the ejector nozzle tube and connecting to an interior of the ejector nozzle tube formed by the hollow profile. An aircraft engine has an optimized oil heat exchanger with at least one oil cooler disposed in a trailing-edge area of an aerofoil-type structure, with at least one flow entrance area being provided to supply ambient air to the oil cooler disposed in a flow duct. The ejector nozzle tube can be arranged downstream of the oil cooler in the flow duct.
摘要翻译：喷射器喷嘴管沿着其长度具有基本上恒定的基本上椭圆形的中空横截面，其前缘喷嘴具有圆形的外部横截面，其布置在喷射器喷嘴管的流动前缘区域处。前缘喷嘴包括向喷射器喷嘴管的顶侧和底侧施加并连接到由中空轮廓形成的喷射器喷嘴管的内部的多个凹槽。飞机发动机具有优化的油热交换器，其具有设置在翼型结构的后缘区域中的至少一个油冷却器，其中至少一个流入口区域被设置成向设置在流动中的油冷却器提供环境空气管。喷射器喷嘴管可以布置在流动管道中的油冷却器的下游。

4. 发明申请

US20130318945A1 AVIATION GAS TURBINE THRUST REVERSING DEVICE 有权
标题翻译：航空气体涡轮扭转装置
公开(公告)号：US20130318945A1
公开(公告)日：2013-12-05
申请号：US13979782
申请日：2012-01-19
申请人： Predrag Todorovic
发明人： Predrag Todorovic
IPC分类号： F02K3/02
CPC分类号： F02K3/025 , F02K1/64 , F02K1/70 , F02K1/72 , F02K1/763
摘要： The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling, the rear area of which can be displaced in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular free space towards a forward stationary area of the engine cowling, with the rear area of the engine cowling being functionally coupled to deflecting elements arranged in the forward thrust position within the front area of the engine cowling, with the deflecting elements during displacement of the rear area of the engine cowling being moveable on a partial-circular path facing the central axis of the engine and contactable by their rear end areas with a cowling of the core engine.
摘要翻译：本发明涉及一种具有发动机的发动机的飞机燃气轮机推力反向装置，发动机整流罩的后部区域可以从封闭的向前推力位置向后移动的推力反转位置沿发动机的轴向位移，导致朝向发动机整流罩的前部静止区域的基本上环形的自由空间，发动机整流罩的后部区域功能地联接到布置在发动机整流罩前部区域内的向前推力位置的偏转元件，偏转元件在发动机整流罩的后部区域的移动期间可以在面向发动机的中心轴线的部分圆形路径上移动，并且可由其后端区域与核心发动机的整流罩接触。

5. 发明授权

US08561940B2 Arrangement for the suspension of a jet engine to a supporting structure 有权
标题翻译：用于将喷气发动机悬挂到支撑结构的布置
公开(公告)号：US08561940B2
公开(公告)日：2013-10-22
申请号：US12964890
申请日：2010-12-10
申请人： Stephan Lisiewicz , Predrag Todorovic
发明人： Stephan Lisiewicz , Predrag Todorovic
IPC分类号： B64D27/26
CPC分类号： B64D27/14 , B64D27/26 , B64D2027/026 , Y02T50/44
摘要： An arrangement (1) for suspending a jet engine (12) to a supporting structure (5) attached to an aircraft fuselage, includes a suspension beam (6) to which the engine casing (13) is fitted by a forward suspension (7), a rearward suspension (8) and at least one thrust rod (9) arranged at an angle relative to the suspension beam (6). In order to provide an arrangement for the suspension of a jet engine (12) which enables weight to be saved and deformation of the jet engine (12) to be reduced, the rearward suspension (8) and the thrust rod (9) are connected to the engine casing (13) by a lightweight framework (11).
摘要翻译：用于将喷气发动机（12）悬挂到附接到飞行器机身的支撑结构（5）上的装置（1）包括悬挂梁（6），发动机壳体（13）由前悬架（7）装配到该悬挂梁，后悬架（8）和至少一个相对于悬挂梁（6）成一定角度布置的推杆（9）。为了提供喷气发动机（12）的悬挂装置，其能够节省重量并减少喷气发动机（12）的变形，则后悬架（8）和推杆（9）被连接通过轻型框架（11）到发动机壳体（13）。

6. 发明授权

US08480032B2 Aircraft de-icing device and engine nacelle of an aircraft gas turbine with de-icing device 有权
标题翻译：具有除冰装置的飞机燃气轮机的飞机除冰装置和发动机舱
公开(公告)号：US08480032B2
公开(公告)日：2013-07-09
申请号：US12939609
申请日：2010-11-04
申请人： Predrag Todorovic
发明人： Predrag Todorovic
IPC分类号： B64D15/02
CPC分类号： B64D15/04 , B64D29/00 , B64D33/02 , B64D33/10 , B64D2033/0233
摘要： An aircraft de-icing device and an engine nacelle of an aircraft gas turbine is provided with a de-icing device, with the engine nacelle 1 in the inflow area being provided with an annular air duct 2, into which heated air is introduced. At least one oil cooler 3 is arranged in the engine nacelle 1, to which engine oil is fed and which is supplied with ambient air, with the heated airflow leaving the oil cooler 3 being passed through the air duct 2.
摘要翻译：飞机除冰装置和飞机燃气轮机的发动机舱设置有除冰装置，发动机舱1在流入区域中设置有环形空气管道2，加热的空气被引入该环形空气管道2中。至少一个油冷却器3布置在发动机舱1中，发动机机油被供给到其中并且被供给环境空气，而流过油冷却器3的加热空气通过空气管道2。

7. 发明申请

US20110139925A1 ARRANGEMENT FOR THE SUSPENSION OF A JET ENGINE TO A SUPPORTING STRUCTURE 有权
标题翻译：喷气式发动机悬挂支援结构的安排
公开(公告)号：US20110139925A1
公开(公告)日：2011-06-16
申请号：US12964890
申请日：2010-12-10
申请人： Stephan LISIEWICZ , Predrag TODOROVIC
发明人： Stephan LISIEWICZ , Predrag TODOROVIC
IPC分类号： B64D27/20
CPC分类号： B64D27/14 , B64D27/26 , B64D2027/026 , Y02T50/44
摘要： An arrangement (1) for suspending a jet engine (12) to a supporting structure (5) attached to an aircraft fuselage, includes a suspension beam (6) to which the engine casing (13) is fitted by a forward suspension (7), a rearward suspension (8) and at least one thrust rod (9) arranged at an angle relative to the suspension beam (6). In order to provide an arrangement for the suspension of a jet engine (12) which enables weight to be saved and deformation of the jet engine (12) to be reduced, the rearward suspension (8) and the thrust rod (9) are connected to the engine casing (13) by a lightweight framework (11).
摘要翻译：用于将喷气发动机（12）悬挂到附接到飞行器机身的支撑结构（5）上的装置（1）包括悬挂梁（6），发动机壳体（13）由前悬架（7）装配到该悬挂梁，后悬架（8）和至少一个相对于悬挂梁（6）成一定角度布置的推杆（9）。为了提供喷气发动机（12）的悬挂装置，其能够节省重量并减少喷气发动机（12）的变形，则后悬架（8）和推杆（9）被连接通过轻型框架（11）到发动机壳体（13）。

8. 发明授权

US08938944B2 Aircraft gas-turbine engine with oil cooler in the engine cowling 有权
标题翻译：发动机整流罩内装有油冷却器的飞机燃气涡轮发动机
公开(公告)号：US08938944B2
公开(公告)日：2015-01-27
申请号：US13468483
申请日：2012-05-10
申请人： Predrag Todorovic
发明人： Predrag Todorovic
IPC分类号： F02K99/00 , F02K3/02 , F02K1/54 , B63H11/10 , F01D25/18 , F02C7/14 , F02K1/72 , B64D29/00 , B64D33/10
CPC分类号： F02C7/14 , B64D29/00 , B64D33/10 , F02K1/72 , F05D2260/20 , Y02T50/676
摘要： The present invention relates to an aircraft gas-turbine engine with a core engine surrounded by a bypass duct, with a radially outer engine cowling enclosing the bypass duct and being provided at its rear region with a thrust-reversing device which is moveable relative to the engine cowling, with at least one cooler element extending over at least part of the circumference being arranged in the intermediate area between the engine cowling and the thrust-reversing device.
摘要翻译：技术领域本发明涉及一种具有由旁路管道围绕的核心发动机的飞机燃气涡轮发动机，其中包围旁路管道的径向外部发动机整流罩，并且在其后部区域处设置有推力反转装置，该推力反向装置可相对于发动机整流罩，其中至少一个在圆周的至少一部分上延伸的冷却器元件布置在发动机整流罩和推力反向装置之间的中间区域中。

9. 发明授权

US08833515B2 Method for the production of a sound absorber, especially for a gas turbine exhaust cone 有权
标题翻译：用于制造吸声器的方法，特别是用于燃气轮机排气锥体的方法
公开(公告)号：US08833515B2
公开(公告)日：2014-09-16
申请号：US13979809
申请日：2012-01-19
申请人： Predrag Todorovic
发明人： Predrag Todorovic
IPC分类号： F02K1/00 , F02K1/82 , F01D25/30 , F02C7/24
CPC分类号： F02C7/24 , F01D25/30 , F02K1/00 , F02K1/827 , F05D2260/96 , Y10T29/49826
摘要： The present invention relates to a method for manufacturing a body provided with a honeycomb structure, which body is designed preferably axis-symmetrical, with sheet-metal parts being provided with a wave-like structuring by means of a forming process and formed to ring elements, with the sheet-metal parts being shaped and designed in a substantially identical way as regards their structuring, with adjacent sheet-metal parts being arranged offset to one another and then joined together to form the honeycomb structure.
摘要翻译：本发明涉及一种具有蜂窝结构体的制造方法，该主体被设计为优选为轴对称的，其中金属片部件通过成形工艺设置成波状结构，并形成为环形元件其中钣金部件以与其结构相同的方式成形和设计，相邻的钣金部件彼此偏移地布置，然后连接在一起以形成蜂窝结构体。

10. 发明授权

US08783412B2 Sound absorber for a gas turbine exhaust cone, and method for the production thereof 有权
标题翻译：燃气轮机排气锥体的吸声器及其制造方法
公开(公告)号：US08783412B2
公开(公告)日：2014-07-22
申请号：US13980018
申请日：2012-01-19
申请人： Predrag Todorovic
发明人： Predrag Todorovic
IPC分类号： F02K1/82 , B64D33/02 , B64D33/04 , F01D25/30 , F02C7/24 , F02K1/44 , F02C7/045 , F01N13/00 , F02K1/78 , B64D33/00
CPC分类号： F01N13/00 , F01D25/30 , F02C7/045 , F02C7/24 , F02K1/44 , F02K1/827 , F05D2250/283 , F05D2260/96 , Y10T29/4957
摘要： A method for manufacturing a sound absorber, the outer wall of which is provided with a plurality of recesses, with funnel-like cone elements each being assigned to the recesses inside the sound absorber, said cone elements having a larger opening facing radially outwards and a smaller opening facing radially inwards, with adjacent cone elements each being provided on a strip-shaped first carrier band, with cup elements being provided radially on the inside relative to the cone elements, and each cup element receiving one cone element, with adjacent cup elements each being provided on a strip-shaped first carrier band, with the first carrier bands being arranged adjacently in a first direction, and the second carrier bands being arranged adjacently in a second direction, with the directions crossing each other and the carrier bands being joined to one another and to the outer wall to form a rigid body.
摘要翻译：一种用于制造吸声器的方法，其外壁上设有多个凹槽，漏斗状锥形元件分别被分配到吸声器内部的凹部，所述锥形元件具有朝向径向向外的较大的开口和较小的开口朝向径向向内，相邻的锥形元件各自设置在带状的第一载体带上，其中杯形元件相对于锥形元件径向地设置在内部，并且每个杯形元件接收一个锥形元件，其中相邻的杯形元件每个都设置在带状的第一载波带上，其中第一载波带在第一方向上相邻布置，并且第二载波带沿第二方向相邻地布置，并且载波带被连接彼此并且到外壁以形成刚体。

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