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12 条记录 (耗时 0.013 秒)

    ARRANGEMENT FOR THE SUSPENSION OF A JET ENGINE TO A SUPPORTING STRUCTURE
    1.
    发明申请
    ARRANGEMENT FOR THE SUSPENSION OF A JET ENGINE TO A SUPPORTING STRUCTURE 有权
    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）。

    AIRCRAFT DE-ICING DEVICE AND ENGINE NACELLE OF AN AIRCRAFT GAS TURBINE WITH DE-ICING DEVICE
    2.
    发明申请
    AIRCRAFT DE-ICING DEVICE AND ENGINE NACELLE OF AN AIRCRAFT GAS TURBINE WITH DE-ICING DEVICE 有权
    具有检测装置的飞机气体涡轮机的飞机检测装置和发动机

    公开(公告)号：US20110121136A1

    公开(公告)日：2011-05-26

    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 ,  F01M5/00

    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。

    NOISE-REDUCED AIRCRAFT ENGINE AND METHOD FOR REDUCING NOISE EMISSIONS OF AN AIRCRAFT ENGINE
    3.
    发明申请
    NOISE-REDUCED AIRCRAFT ENGINE AND METHOD FOR REDUCING NOISE EMISSIONS OF AN AIRCRAFT ENGINE 有权
    噪音减少的飞机发动机和减少飞机发动机噪声排放的方法

    公开(公告)号：US20110005858A1

    公开(公告)日：2011-01-13

    申请号：US12818389

    申请日：2010-06-18

    申请人： Predrag TODOROVIC

    发明人： Predrag TODOROVIC

    IPC分类号： F02K1/44

    CPC分类号： B64D33/06

    摘要： A method for reducing noise emissions of an aircraft engine (3) having a gas turbine (7), includes providing a hot gas layer underneath at least one noise-emitting area of the aircraft engine.

    摘要翻译： 一种用于减少具有燃气轮机（7）的飞机发动机（3）的噪声排放的方法，包括在所述飞行器发动机的至少一个噪声发射区域的下方提供热气体层。

    Aircraft gas turbine with variable bypass nozzle
    6.
    发明申请
    Aircraft gas turbine with variable bypass nozzle 有权
    具有可变旁路喷嘴的飞机燃气轮机

    公开(公告)号：US20130008147A1

    公开(公告)日：2013-01-10

    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： F02K3/02 ,  F02K1/08

    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 10 which is surrounded by a bypass duct 29 enclosed radially outwards by a bypass wall 30, with a radially inner wall 31 of the bypass duct 29 forming with the radially outer bypass wall 30 a bypass nozzle 32, and with the radially inner wall 31 including an adjusting element 33 extending along the circumference of the inner wall 31 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10的飞机燃气轮机，其由旁路管道29围绕的旁路管道29围绕，旁路管道29的径向内壁31与径向外部旁路壁30形成 旁路喷嘴32，并且径向内壁31包括沿着内壁31的圆周延伸并且可径向向外变形的调节元件33。

    De-icing device of an aircraft gas-turbine engine
    7.
    发明申请
    De-icing device of an aircraft gas-turbine engine 有权
    飞机燃气轮机的除冰装置

    公开(公告)号：US20120298802A1

    公开(公告)日：2012-11-29

    申请号：US13478261

    申请日：2012-05-23

    申请人： Predrag TODOROVIC

    发明人： Predrag TODOROVIC

    IPC分类号： B64D15/02

    CPC分类号： B64D15/04 ,  B64D33/02 ,  F02C7/047 ,  F05D2240/40

    摘要： The present invention relates to a de-icing device of an aircraft gas-turbine engine with an engine cowling enclosing at least one inflow region, with the engine cowling having a double-walled design and including at least one annular tube element extending in the circumferential direction and being provided with outlet openings for passing hot air to an inflow region, in order to de-ice it, with the tube element in the circumferential direction including multiple individual tube segments which can be attached relative to one another.

    摘要翻译： 本发明涉及一种具有封闭至少一个流入区域的发动机整流罩的飞机燃气涡轮发动机的除冰装置，其中发动机整流罩具有双壁设计，并且包括至少一个在周向延伸的环形管件 方向并且设置有用于将热空气传递到流入区域的出口，以便使其在周向上的管元件脱冰，包括可以相对于彼此附接的多个单独的管段。

    GAS-TURBINE EXHAUST CONE
    8.
    发明申请
    GAS-TURBINE EXHAUST CONE 有权
    气涡轮排气

    公开(公告)号：US20120006614A1

    公开(公告)日：2012-01-12

    申请号：US13180073

    申请日：2011-07-11

    申请人： Predrag TODOROVIC

    发明人： Predrag TODOROVIC

    IPC分类号： F02K1/00

    CPC分类号： F02K1/34 ,  F02K1/44 ,  F02K1/827 ,  F05D2250/232 ,  F05D2250/25 ,  Y02T50/671

    摘要： A gas-turbine exhaust cone includes a cone shaped outside cone 1 closed in a flow direction, an inside cone 2 arranged in the outside cone 1 over at least part of the length of the exhaust cone, with the inside cone 2 being connected to the outside cone 1 via at least one helical partition wall 3, thereby forming an interspace 4 between the outside cone 1 and the inside cone 2. The interspace 4 is connected to inlet openings 5 at its inflow side and opens at an exit side 6 towards an interior 7 of the outside cone 1. A dampening element 8 is arranged in the outside cone 1 adjacent to the exit side 6 of the interspace 4.

    摘要翻译： 燃气轮机排气锥体包括在流动方向上封闭的锥形外锥体1，内锥体2布置在外锥体1的至少部分长度的排气锥体上，内圆锥体2连接到 外锥体1经由至少一个螺旋分隔壁3，从而在外圆锥体1和内圆锥体2之间形成间隙4.间隙4在其入流侧连接到入口开口5，并在出口侧6朝向 外圆锥体1的内部7。阻尼元件8布置在邻近间隙4的出口侧6的外锥体1中。

    Aircraft engine with optimized oil heat exchanger
    9.
    发明申请
    Aircraft engine with optimized oil heat exchanger 有权
    具有优化油热交换器的飞机发动机

    公开(公告)号：US20110215172A1

    公开(公告)日：2011-09-08

    申请号：US13039795

    申请日：2011-03-03

    申请人： Predrag TODOROVIC

    发明人： Predrag TODOROVIC

    IPC分类号： B63H11/10

    CPC分类号： B64D27/14 ,  B64D29/04 ,  B64D33/10 ,  B64D2027/005 ,  B64D2027/026 ,  Y02T50/66

    摘要： This invention relates town ejector nozzle tube 1, having along its length an essentially constant, essentially oval hollow cross-section, with an inflow lip 2, having a pitch-circle type cross-section, being arranged at a flow leading-edge area of the ejector nozzle tube 1. The inflow lip 2 is provided with a plurality of grooves 3 issuing (4) to the top and bottom sides of the ejector nozzle tube 1 and connecting to an interior 5 of the ejector nozzle tube 1 formed by the hollow profile. It also relates to an aircraft engine with optimized oil heat exchanger with at least one oil cooler 6 disposed in a trailing-edge area 7 of an aerofoil-type structure 8, with at least one flow entrance area 9 being provided to supply ambient air to the oil cooler 6 disposed in a flow duct 10, and with an ejector nozzle tube 1 in accordance with one of the claims 1 to 3 being arranged downstream of the oil cooler 6 in the flow duct 10.

    摘要翻译： 本发明涉及城市喷射器喷嘴管1，其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，其具有节圆型横截面的流入凸缘2，其布置在流动前缘区域 喷射器喷嘴管1.流入口2设置有多个槽3，其向喷射器喷嘴管1的顶侧和底侧发出（4），并连接到由中空部形成的喷射器喷嘴管1的内部5 个人资料 它还涉及具有优化的油热交换器的飞机发动机，其具有设置在机翼型结构8的后缘区域7中的至少一个油冷却器6，其中至少一个流入口区域9被提供以将周围空气供应到 设置在流动管道10中的油冷却器6和根据权利要求1至3中任一项所述的喷射器喷嘴管1布置在流动管道10中的油冷却器6的下游。

    Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element
    10.
    发明申请
    Gas-turbine exhaust cone with three-dimensionally profiled partition wall and plate-type wall element 有权
    燃气轮机排气锥具有三维异型隔墙和板式墙体元件

    公开(公告)号：US20130025962A1

    公开(公告)日：2013-01-31

    申请号：US13555790

    申请日：2012-07-23

    申请人： Predrag TODOROVIC

    发明人： Predrag TODOROVIC

    IPC分类号： F02K1/82

    CPC分类号： F02K1/04 ,  F02K1/827 ,  F05D2250/28 ,  F05D2250/61 ,  F05D2250/611 ,  F05D2260/96

    摘要： A gas-turbine exhaust cone has an outer wall with a plurality of recesses, a honeycomb-structured layer arranged at the inside of the outer wall and extending along said inside of the outer wall, an inner wall connected to the honeycomb structure and extending essentially parallel to the outer wall, and at least one annular chamber centered on a central axis and adjoining the inner wall. The inner wall has passage recesses connecting the area of the honeycomb structure to the annular chamber, with the annular chamber being subdivided in the circumferential direction by at least one partition wall into several chambers. The partition wall is made from a sheetmetal-like material and has a plurality of raised and/or recessed areas in a uniform arrangement formed by shaping of the sheetmetal-like material.

    摘要翻译： 燃气轮机排气锥体具有外壁，该外壁具有多个凹部，蜂窝结构层布置在外壁的内侧并且沿着外壁的内侧延伸，内壁连接到蜂窝结构并基本上延伸 平行于外壁，以及至少一个以中心轴为中心并邻接内壁的环形室。 内壁具有将蜂窝结构的区域连接到环形室的通道凹部，环形室在圆周方向上被至少一个分隔壁细分成几个室。 分隔壁由片状金属材料制成，并且具有多个凸起和/或凹陷区域，该区域以通过成形该片状金属材料形成的均匀布置形成。