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    Compressor and a turbine engine with optimized efficiency
    1.
    发明授权
    Compressor and a turbine engine with optimized efficiency 有权
    压缩机和优化效率的涡轮发动机

    公开(公告)号：US09488179B2

    公开(公告)日：2016-11-08

    申请号：US13703809

    申请日：2011-06-09

    申请人： Vincent Paul Gabriel Perrot ,  Agnes Pesteil ,  Lieven Baert ,  Vasiliki Iliopoulou

    发明人： Vincent Paul Gabriel Perrot ,  Agnes Pesteil ,  Lieven Baert ,  Vasiliki Iliopoulou

    IPC分类号： F04D29/00 ,  F04D19/00 ,  F04D29/54 ,  F04D29/68 ,  F01D5/14 ,  F01D5/20 ,  F04D29/52

    CPC分类号： F04D19/00 ,  F01D5/143 ,  F01D5/145 ,  F01D5/20 ,  F04D29/522 ,  F04D29/526 ,  F04D29/545 ,  F04D29/547 ,  F04D29/68 ,  F04D29/681 ,  F05D2250/232 ,  F05D2250/314 ,  F05D2260/2212

    摘要： A turbine engine compressor including a casing having its inside wall defining an aerodynamic reference surface for a gas-passing passage and in which a rotor wheel having radial blades is mounted. A circumferential trench is formed in the inside wall of the casing. Its shape is defined from upstream to downstream by three surfaces, respectively an upstream surface, a middle surface, and a downstream surface, which surfaces are substantially conical. The upstream surface extends upstream from the leading edges of the blades. The middle surface is substantially parallel to the aerodynamic reference surface. The downstream surface extends downstream at least as far as the trailing edges of the blades. The junction between the middle and downstream surfaces is in a range of 30% to 80% or 50% to 65% of the axial length of the blades starting from their leading edges.

    摘要翻译： 一种涡轮发动机压缩机，包括壳体，其内壁限定用于气体通过通道的空气动力参考表面，并且其中安装有具有径向叶片的转子轮。 在壳体的内壁中形成周向沟槽。 其形状从上游到下游分别由上游表面，中间表面和下游表面三个表面限定，该表面基本上是圆锥形的。 上游表面从叶片的前缘向上延伸。 中间表面基本上平行于空气动力学参考表面。 下游表面至少延伸到叶片的后缘的下游。 中间和下游表面之间的连接处在从其前缘开始的叶片的轴向长度的30％至80％或50％至65％的范围内。

    SHORT IMPELLER FOR A TURBOMACHINE
    3.
    发明申请
    SHORT IMPELLER FOR A TURBOMACHINE 审中-公开

    公开(公告)号：US20180223875A1

    公开(公告)日：2018-08-09

    申请号：US15927117

    申请日：2018-03-21

    申请人： OneSubsea IP UK Limited

    发明人： Bernt-Helge Torkildsen

    IPC分类号： F04D29/68 ,  F04D29/32 ,  F04D29/18 ,  E21B43/01

    CPC分类号： F04D29/68 ,  E21B43/01 ,  E21B43/121 ,  F04D1/06 ,  F04D13/086 ,  F04D29/185 ,  F04D29/321 ,  F04D29/324 ,  F04D29/682 ,  F04D29/684 ,  F04D29/688

    摘要： A subsea fluid pressure-increasing machine includes an elongated member that is rotatable about a longitudinal axis. The machine also may include a plurality of impellers each having a leading edge, a trailing edge, a suction side, and a chord line defined by a line between the leading and trailing edges. Each impeller is fixedly mounted to the member such that a chord angle defined by an angle between the chord line and the rotation direction is less than or equal to a stall angle at which a maximum force is exerted on a fluid in a direction primarily parallel to the longitudinal axis when the member is rotated in the rotation direction. At least some of the impellers comprise one or more features that effectively reduce a pressure peak or specific loading of the suction side such that the axial length of the impeller is configured to be reduced without exceeding a desired specific load.

    Method and apparatus for producing fluid pressure and controlling boundary layer
    4.
    发明授权
    Method and apparatus for producing fluid pressure and controlling boundary layer 失效
    用于生产流体压力和控制边界层的方法和装置

    公开(公告)号：US5152661A

    公开(公告)日：1992-10-06

    申请号：US513495

    申请日：1990-04-20

    申请人： Herman E. Sheets

    发明人： Herman E. Sheets

    IPC分类号： F01D5/14 ,  F04D29/18 ,  F04D29/30 ,  F04D29/38 ,  F04D29/44 ,  F04D29/54 ,  F04D29/68

    CPC分类号： F04D29/18 ,  F01D5/145 ,  F01D5/146 ,  F04D29/30 ,  F04D29/384 ,  F04D29/44 ,  F04D29/544 ,  F04D29/68

    摘要： This invention relates to a blower of a centrifugal turbomachine type for producing fluid pressure from mechanical energy. The invention relates to the guide vane rows or vaned diffuser used in centrifugal blowers. The vaned diffuser is located downstream by the impeller. The impellers of the centrifugal blowers can have blades which are backwardly curved, radially ending or forwardly curved. Each of these impellers can have a vaned or vaneless diffusing system following the impeller. During operation of the impeller blades at the design point, the average outlet relative velocity is equal to or greater than 0.6 times the inlet relative velocity at the hub of the impeller portion of the impeller blades and the angle of flow deflection within the impeller blades is at least equal to approximately 50.degree. or more. The centrifugal turbomachine also includes a series of guide vane rows, each of said guide vane rows, including at least a forward row of blades and an aft row of blades. The chord of each of the blades in the aft row is greater than the chord of each of the blades in the forward row and each blade in the aft row cooperates with the corresponding blade in the forward row to form, during operation of the centrifugal turbomachine, multiple rows of blades. The pressure coefficient for each centrifugal blower stage is greater than approximately 1.1.

    摘要翻译： 本发明涉及一种用于从机械能产生流体压力的离心涡轮机类型的鼓风机。 本发明涉及用于离心式鼓风机的导向叶片排或叶片式扩散器。 带叶片的扩散器位于叶轮的下游。 离心鼓风机的叶轮可以具有向后弯曲，径向结束或向前弯曲的叶片。 这些叶轮中的每一个可以具有跟随叶轮的叶片或无叶漫射系统。 在设计时叶轮叶片的操作期间，平均出口相对速度等于或大于叶轮叶轮叶轮部分的轮毂处的入口相对速度的0.6倍，并且叶轮叶片内的流动偏转角度 至少等于大约50°以上。 离心涡轮机还包括一系列导向叶片排，每个所述导向叶片排，至少包括一排叶片和一排叶片。 后排中每个叶片的弦大于前排中每个叶片的弦，并且后排中的每个叶片与前排中的相应叶片协作，以在离心涡轮机的操作期间形成 ，多行刀片。 每个离心鼓风机级的压力系数大于约1.1。

    CIRCUMFERENTIALLY VARYING AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN
    7.
    发明申请
    CIRCUMFERENTIALLY VARYING AXIAL COMPRESSOR ENDWALL TREATMENT FOR CONTROLLING LEAKAGE FLOW THEREIN 审中-公开
    循环式轴流式压缩机终端处理，用于控制泄漏流量

    公开(公告)号：US20160169017A1

    公开(公告)日：2016-06-16

    申请号：US14572119

    申请日：2014-12-16

    申请人： General Electric Company

    发明人： Davide Giacché ,  John David Stampfli ,  Ramakrishna Venkata Mallina ,  Vittorio Michelassi ,  Giridhar Jothiprasad ,  Ajay Keshava Rao ,  Rudolf Konrad Selmeier ,  Sungho Yoon ,  Ivan Malcevic

    IPC分类号： F01D11/00 ,  F02C3/04

    CPC分类号： F01D11/001 ,  F04D27/02 ,  F04D29/526 ,  F04D29/68 ,  F04D29/681 ,  F04D29/685

    摘要： A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

    摘要翻译： 一种用于燃气涡轮发动机的压缩机，其包括用于控制压缩机中的泄漏流动和周向流动不均匀性的一个或多个端壁处理。 压缩机包括壳体，毂，形成在壳体和轮毂之间的流动路径，位于流动路径中的多个叶片，以及形成在至少一个的内表面中的一个或多个周向变化的端壁处理 套管或轮毂。 一个或多个周向变化的端壁处理中的每一个基于它们与紧邻的上游bladerow的相对位置周向地变化。 一个或多个端壁处理中的每一个在相对于直接相邻的上游bladerow的放置中的至少一个中或在限定多个周向变化的端壁处理中的每一个的几何参数中的周向变化。 另外公开了一种包括压缩机的发动机。

    Friction reducing arrangement for hydraulic machines
    8.
    发明授权
    Friction reducing arrangement for hydraulic machines 失效
    液压机减摩装置

    公开(公告)号：US4236867A

    公开(公告)日：1980-12-02

    申请号：US61777

    申请日：1979-07-27

    申请人： Joseph H. Morris

    发明人： Joseph H. Morris

    IPC分类号： F01D11/04 ,  F04D29/68 ,  F01D11/00

    CPC分类号： F01D11/04 ,  F04D29/68

    摘要： A hydraulic machine comprising a rotor concentrically supported in a fluidhamber of the housing wherein upper and lower annular fluid spaces defined between the rotor and housing include upper cavity regions formed radially adjacent the rotor axis and lower cavity regions declined radially therefrom. Fluid supply ports in the upper cavity regions of the annular spaces permit flow of a relatively low density pressurized fluid into the annular spaces to control the level of pumped fluid therein and seal elements span the upper regions of the annular spaces for maintaining pressure differentials between the annular spaces and fluid passages of the housing. Clearance gaps, defined by circumferential edges of the rotor and adjacent surfaces of the fluid chamber, radially bound the lower cavity regions of the annular spaces for limiting the flow of pumped fluid into and out of the annular spaces.

    摘要翻译： 一种液压机械，包括同心地支撑在所述壳体的流体室中的转子，其中限定在所述转子和壳体之间的上部和下部环形流体空间包括径向地邻近所述转子轴线形成的上空腔区域，并且所述下部空腔区域从其径向地下降。 环形空间的上腔区域中的流体供应端口允许相对低密度的加压流体流入环形空间以控制其中的泵送流体的水平，并且密封元件跨越环形空间的上部区域，以保持在 壳体的环形空间和流体通道。 由转子的圆周边缘和流体室的相邻表面限定的间隙可径向地限定环形空间的下腔区域，以限制泵送的流体流入和流出环形空间。