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    COMPRESSOR AND GAS TURBINE
    52.
    发明申请
    COMPRESSOR AND GAS TURBINE 审中-公开
    压缩机和气体涡轮机

    公开(公告)号：US20160131158A1

    公开(公告)日：2016-05-12

    申请号：US14896771

    申请日：2014-02-05

    申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

    发明人： Thomas WALKER

    IPC分类号： F04D29/54 ,  F04D19/02 ,  F02C3/045

    CPC分类号： F04D29/545 ,  F02C3/045 ,  F02C6/08 ,  F04D19/02 ,  F04D29/541 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183

    摘要： This compressor is provided with: a rotor casing that encircles a rotor, which rotates around a rotational axis; an air bleed chamber casing that is provided to the outer peripheral side of the rotor casing and demarcates an air bleed chamber interconnecting to a primary duct via a slot; and an air bleed tube that is connected to the air bleed chamber casing from the outer peripheral side and is provided with an air bleed pathway. In the slot, at which an opening to the primary duct is formed, a large opening, at which the opening area of the opening is locally larger than that of the other positions in the peripheral direction of the opening, is formed at a position in the peripheral direction corresponding to the position at which the air bleed tube is provided.

    摘要翻译： 该压缩机设置有：围绕转子旋转的转子的转子壳体; 设置在所述转子壳体的外周侧的排气室壳体，并且经由槽划分与主管道相互连接的排气室; 以及从外周侧与排气室壳体连接的排气管，设有排气通路。 在形成有主开口的开口的狭槽中，形成开口的开口面积比开口的周向的其他位置局部大的开口部， 所述圆周方向对应于设置放气管的位置。

    Nozzle with guiding devices
    53.
    发明授权
    Nozzle with guiding devices 有权
    喷嘴带导向装置

    公开(公告)号：US09279387B2

    公开(公告)日：2016-03-08

    申请号：US14072073

    申请日：2013-11-05

    申请人： Rolls-Royce Deutschland Ltd & Co KG

    发明人： Marco Rose ,  Rene Spieweg

    IPC分类号： F02K1/00 ,  F02K1/46 ,  F02K1/38 ,  F02K1/48

    CPC分类号： F02K1/46 ,  F02K1/386 ,  F02K1/48 ,  F05D2230/80 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2260/96 ,  Y02T50/671

    摘要： A nozzle has a nozzle surface area and a nozzle rim, on which first and second guiding devices are alternatingly provided in the circumferential direction, where the first guiding devices are of the nozzle-type design and the second guiding devices are of the diffuser-type design. The first guiding devices each have a first azimuthal guide wall and two wall elements. The second guiding devices each have a second azimuthal guide wall and two wall elements. A wall element connects a first guiding device and a second guiding device. At least some of the first azimuthal guide walls of the first guiding device and at least some of the second azimuthal guide walls of the second guiding device have differing axial lengths, so that first and second trailing edges thereof have differing axial positions.

    摘要翻译： 喷嘴具有喷嘴表面积和喷嘴边缘，第一和第二引导装置在圆周方向上交替地设置有第一和第二引导装置，其中第一引导装置是喷嘴型设计，并且第二引导装置是扩散型 设计。 第一引导装置各自具有第一方位引导壁和两个壁元件。 第二引导装置各具有第二方位引导壁和两个壁元件。 壁元件连接第一引导装置和第二引导装置。 第一导向装置的第一方位导向壁和第二导向装置的至少一些第二方位引导壁中的至少一些具有不同的轴向长度，使得其第一和第二后缘具有不同的轴向位置。

    Turbine abradable layer with zig zag groove pattern
    54.
    发明授权
    Turbine abradable layer with zig zag groove pattern 有权
    具有锯齿形凹槽图案的涡轮磨损层

    公开(公告)号：US09243511B2

    公开(公告)日：2016-01-26

    申请号：US14189081

    申请日：2014-02-25

    申请人： Siemens Aktiengesellschaft

    发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Gm Salam Azad

    IPC分类号： F01D11/12

    CPC分类号： F01D11/122 ,  F01D5/02 ,  F01D5/12 ,  F01D11/14 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/30 ,  F05D2230/10 ,  F05D2230/60 ,  F05D2240/24 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/282 ,  F05D2250/294 ,  F05D2250/71 ,  Y10T29/49236

    摘要： Turbine and compressor casing abradable component embodiments for turbine engines, with zig-zag pattern abradable surface ridges and grooves. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Ridge or rib embodiments have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.

    摘要翻译： 用于涡轮发动机的涡轮机和压缩机壳体可磨损部件实施例，具有锯齿形图案可磨损的表面脊和凹槽。 一些实施方案包括明显的前向上游和后向下游复合多取向凹槽和垂直突出的脊平台形图案，以减少，重定向和/或阻挡下游进入凹槽的叶片尖端气流泄漏，而不是从涡轮叶片翼型件到高压侧。 脊或肋实施例具有第一下部和第二上部耐磨区域。 下部区域优化发动机气流特性，同时优化上部区域以通过比下部区域更容易磨损来最小化叶片尖端间隙和磨损。

    SAW TEETH TURBULATOR FOR TURBINE AIRFOIL COOLING PASSAGE
    55.
    发明申请
    SAW TEETH TURBULATOR FOR TURBINE AIRFOIL COOLING PASSAGE 有权
    用于涡轮机空气冷却通风的SAW TEETH TURBULATOR

    公开(公告)号：US20150275676A1

    公开(公告)日：2015-10-01

    申请号：US14159817

    申请日：2014-01-21

    申请人： Siemens Energy, Inc.

    发明人： George Liang

    IPC分类号： F01D5/18 ,  F01D5/14

    CPC分类号： F01D5/18 ,  F01D5/147 ,  F01D5/187 ,  F05D2250/11 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/21 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

    摘要： A trip strip having a saw-tooth configuration that has application for cooling flow channels in a blade of a gas turbine engine. The saw-tooth configuration is defined by trip strip sections positioned end-to-end, where a leading edge of a trip strip section has a lower height than a trailing end of the trip strip section, and where the next trip strip section having the lower height leading edge disrupts the vortex created by the preceding trip strip section so that its size is reduced.

    摘要翻译： 具有锯齿结构的跳闸带，其具有用于冷却燃气涡轮发动机的叶片中的流动通道的应用。 锯齿配置由端对端定位的跳闸带部分限定，其中跳闸带部分的前缘具有比跳闸带部分的尾端低的高度，并且其中下一跳闸带段具有 较低的高度前缘破坏由前一跳闸带部分产生的涡流，使其尺寸减小。

    LEAF SEAL
    57.
    发明申请
    LEAF SEAL 有权
    LEAF密封

    公开(公告)号：US20150001808A1

    公开(公告)日：2015-01-01

    申请号：US14317651

    申请日：2014-06-27

    申请人： ROLLS-ROYCE PLC

    发明人： Gervas FRANCESCHINI ,  David Anthony EDWARDS

    IPC分类号： F16J15/32 ,  F01D11/00

    CPC分类号： F16J15/3292 ,  F01D11/00 ,  F01D11/001 ,  F05D2240/57 ,  F05D2240/59 ,  F05D2250/183 ,  F16J15/3288 ,  Y10T29/49297

    摘要： A leaf seal is proposed for effecting a seal between two coaxial and relatively rotating components. The seal has an annular pack of stacked leaves, the pack being mountable to a first one of the components at root portions of the leaves and extending towards the other component such that end edges of the leaves cooperate to define a seal surface of the pack which is presented for air-riding interaction with a surface of the other component during relative rotation between the components such that, in use, a pressure drop is maintained axially across the pack. The seal surface of the pack incorporates a plurality of hydrodynamic lift-generating recesses spaced circumferentially around the pack. Each said recess extends circumferentially across a plurality of adjacent leaves in the pack, each of which leaves being spaced radially from said surface of the other component along at least part of its end edge.

    摘要翻译： 提出了用于实现两个同轴和相对旋转部件之间的密封的叶密封件。 密封件具有一堆叠的叶片的环形包装，该包装件可安装到叶片的根部处的第一个部件并朝向另一个部件延伸，使得叶片的端部边缘协作以限定包装的密封表面， 被呈现为在组件之间的相对旋转期间与另一部件的表面进行空气相互作用，使得在使用中，压降沿轴向保持在包装上。 包装的密封表面包括围绕包装件周向间隔开的多个流体动力提升产生凹部。 每个所述凹部周向延伸穿过所述包装中的多个相邻的叶片，每个叶片沿其端部边缘的至少一部分离开另一部件的所述表面径向间隔开。

    TURBOFAN ENGINE MIXER ASSEMBLY
    58.
    发明申请
    TURBOFAN ENGINE MIXER ASSEMBLY 有权
    涡轮发动机混合器总成

    公开(公告)号：US20130104555A1

    公开(公告)日：2013-05-02

    申请号：US13285826

    申请日：2011-10-31

    申请人： Mustafa Dindar ,  Vaughn Kunze

    发明人： Mustafa Dindar ,  Vaughn Kunze

    IPC分类号： F02C7/00

    CPC分类号： F02K1/48 ,  F02C7/045 ,  F02K1/386 ,  F05D2250/183

    摘要： A mixer for mixing flows in a turbofan engine is provided. The mixer includes a plurality of chevron lobes, each of the plurality of lobes comprising a crown, a keel, a first trailing edge, a second trailing edge, and a first transverse edge extending between first trailing edge and second trailing edge, said mixer configured to receive two separate incoming exhaust flows and mix the two flows into at least one rotational exhaust flow that is ejected out at least one of said first trailing edge and said second trailing edge.

    摘要翻译： 提供了一种用于混合涡轮风扇发动机的混合器。 混合器包括多个人字形叶片，多个叶片中的每一个叶片包括冠部，龙骨，第一后缘，第二后缘和在第一后缘和第二后缘之间延伸的第一横向边缘，所述混合器配置 以接收两个单独的进入的排气流，并将两个流混合到至少一个旋转排气流中，所述至少一个旋转排气流从所述第一后缘和所述第二后缘中的至少一个排出。

    TRAILING EDGE COOLING SYSTEM IN A TURBINE AIRFOIL ASSEMBLY
    59.
    发明申请
    TRAILING EDGE COOLING SYSTEM IN A TURBINE AIRFOIL ASSEMBLY 有权
    涡轮叶片组件中的边缘冷却系统

    公开(公告)号：US20130064681A1

    公开(公告)日：2013-03-14

    申请号：US13228567

    申请日：2011-09-09

    申请人： Ching-Pang Lee

    发明人： Ching-Pang Lee

    IPC分类号： F01D5/18

    CPC分类号： F01D5/186 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/183 ,  F05D2260/202

    摘要： An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a plurality of cooling fluid passages. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling fluid passages are in fluid communication with the cooling fluid cavity and include zigzagged passages that include alternating angled sections, each section having both a radial component and a chordal component. The cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall and receive cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge.

    摘要翻译： 燃气涡轮发动机中的翼型件包括外壁，冷却流体腔和多个冷却流体通道。 外壁具有前缘，后缘，压力侧，吸力侧以及径向内外端。 冷却流体腔被限定在外壁中，大致径向延伸在外壁的内端和外端之间，并接收用于冷却外壁的冷却流体。 冷却流体通道与冷却流体腔流体连通，并且包括包括交替成角度部分的锯齿形通道，每个部分都具有径向部件和弦部件。 冷却流体通道从冷却流体腔朝向外壁的后缘延伸，并接收来自冷却流体腔的冷却流体，用于冷却靠近后缘的外壁。