中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

347 records (took 0.012 seconds)

    Stator vane assembly and associated methods
    181.
    发明授权
    Stator vane assembly and associated methods 失效
    定子叶片装配及相关方法

    公开(公告)号：US4452564A

    公开(公告)日：1984-06-05

    申请号：US319829

    申请日：1981-11-09

    Applicant: Ronald G. Conant ,  Larry T. Veasey

    Inventor： Ronald G. Conant ,  Larry T. Veasey

    IPC: F01D9/02 ,  F01D9/04 ,  F02C7/04 ,  F02C7/05 ,  F02K3/06 ,  F04D29/54

    CPC classification number: F02K3/06 ,  F01D9/042 ,  F02C7/05 ,  Y02T50/673

    Abstract: An annular inlet stator vane assembly positioned upstream of the bypass and core flow passages of a turbofan jet engine is provided with energy-absorbing bendable vanes which are fixedly secured to an outer support shroud assembly and extended through slots in an inner shroud assembly. The inner ends of the vanes are releasably secured to the inner shroud by specially designed deformable retention clips which are welded to the inner vane ends and shroud. These features of the vane assembly cooperate to limit the circumferential extent of inlet vane damage caused by engine-ingested objects, and to help prevent damaged vane assembly structure from being drawn through the core passage of the engine or blocking such core passage.

    Abstract translation: 位于涡轮风扇喷气发动机的旁路和核心流动通道上游的环形入口定子叶片组件设置有能量吸收可弯曲叶片，其固定地固定到外部支撑罩组件并延伸穿过内部护罩组件中的狭槽。 通过专门设计的可变形保持夹将叶片的内端可释放地固定到内护罩上，焊接到内叶片端和护罩上。 叶片组件的这些特征相辅相成以限制由引擎摄取的物体引起的入口叶片损坏的周向范围，并且有助于防止损坏的叶片组件结构被引导通过发动机的核心通道或堵塞该核心通道。

    Gas turbine engine and its associated air intake system
    182.
    发明授权
    Gas turbine engine and its associated air intake system 失效
    燃气涡轮发动机及其相关进气系统

    公开(公告)号：US4425756A

    公开(公告)日：1984-01-17

    申请号：US347332

    申请日：1982-02-09

    Applicant: John R. Ballard ,  George H. Bennett ,  Leslie A. Lee

    Inventor： John R. Ballard ,  George H. Bennett ,  Leslie A. Lee

    IPC: F02C7/052 ,  F02C7/05

    CPC classification number: F02C7/05 ,  Y02T50/671

    Abstract: A gas turbine engine and its associated air intake system in which the air intake system comprises a generally horizontally extending duct through which an airflow is induced by an ejector pump powered by the engine. A portion of the air passing through the duct is directed through a second duct to the air inlet of the engine. The second duct is connected to the first duct in such a manner that the air directed to the engine air inlet is derived from a vertically upper region of the first duct. The arrangement is intended to reduce the amount of airborne particulate material ingested by the gas turbine engine.

    Abstract translation: 一种燃气涡轮发动机及其相关联的进气系统，其中进气系统包括大致水平延伸的管道，气流由发动机驱动的喷射泵引导通过该管道。 通过管道的空气的一部分通过第二管道被引导到发动机的空气入口。 第二管道以这样的方式连接到第一管道，使得引导到发动机空气入口的空气从第一管道的垂直上部区域获得。 该装置旨在减少由燃气涡轮发动机摄取的空气传播的颗粒物质的量。

    Air intakes
    183.
    发明授权
    Air intakes 失效
    空气吸入

    公开(公告)号：US3684857A

    公开(公告)日：1972-08-15

    申请号：US3684857D

    申请日：1971-01-29

    Applicant: ROLLS ROYCE

    Inventor： MORLEY FREDERICK WILLIAM WALTO ,  BENNETT GEORGE HENRY ,  HARVEY RICHARD GEORGE ,  WILSON ALAN

    IPC: F02C7/05 ,  H05B1/00

    CPC classification number: F02C7/05

    Abstract: A gas turbine engine air intake designed to prevent ingestion into the engine of a substantial proportion of any ice or slush present in the incoming air. The air intake comprises a central bullet and an outer casing defining an annular passage therebetween through which air flows to the engine compressor. The central bullet is enlarged at its upstream end to a mushroom shape whose outer periphery lies upstream of and is at a greater radius than the leading edge of the outer casing. In operation the ice and slush is deflected by reason of its greater momentum around the outside of the engine cowl and out of the path of the air drawn into the annular passage.

    Abstract translation: 一种燃气涡轮发动机空气进气口，其设计用于防止进入发动机的进入空气中存在的任何冰块或冰块的相当大比例的摄入。 进气口包括一个中心子弹和外壳，在其间限定一个环形通道，空气通过空气流向发动机压缩机。 中央子弹在其上游端被扩大为蘑菇形状，其外周位于外壳的前缘的上游并且具有比外壳的前缘更大的半径。 在操作中，冰和冰浆由于其在发动机罩的外部周围较大的动量而偏离被吸入环形通道的空气的路径而偏转。

    Particle separator especially for use in connection with jet engines
    184.
    发明授权
    Particle separator especially for use in connection with jet engines 失效
    颗粒分离器特别适用于喷气发动机

    公开(公告)号：US3616616A

    公开(公告)日：1971-11-02

    申请号：US3616616D

    申请日：1968-03-11

    Applicant: TECH DEV INC

    Inventor： FLATT JOSEPH

    IPC: B04C3/06 ,  F02C7/05 ,  B01D45/12

    CPC classification number: F02C7/05 ,  B04C3/06 ,  B04C2003/006 ,  Y02T50/671

    Abstract: A PARTICLE SEPARATOR, ESPECIALLY FOR USE IN CONNECTION WITH A GAS TURBINE, WHICH COMPRISES COWL MEANS HAVING AN INLET END AND OUTLET END AND TOGETHER WITH A DEFLECTOR BODY ARRANGED WITHIN SAID COWL MEANS IN SPACED RELATIONSHIP THERETO FORMS PASSAGE MEANS EXTENDING FROM SAID INLET MEANS TO SAID OUTLET MEANS WHILE THE OUTER CONTOUR OF SAID DEFLECTOR BODY ASCENDS FROM SAID INLET END TO A HUMP ON THE DEFLECTOR BODY BETWEEN SAID INLET OUTLET END, THAT PORTION OF SAID PASSAGE MEANS WHICH IS LOCATED BETWEEN THE OUTLET END OF SAID COWL MEANS AND THE SAID HUMP BEING DIVIDED INTO AN OUTER PASSAGE FOR DISCHARGING SEPARATED PARTICLE MEANS TO THE ATMOSPHERE AND TO AN INNER PASSAGE FOR DISCHARGING AIR TO A TURBINE ENGINE TO WHICH THE DEFLECTOR IS CONNECTED.

    Super-cooled ice impact protection for a gas turbine engine
    190.
    发明授权
    Super-cooled ice impact protection for a gas turbine engine 有权

    公开(公告)号：US11873731B2

    公开(公告)日：2024-01-16

    申请号：US18114583

    申请日：2023-02-27

    Applicant: ROLLS-ROYCE plc

    Inventor： Ian J. Bousfield ,  Duncan A. Macdougall

    IPC: F01D5/14 ,  F02C7/05 ,  F02C7/36

    CPC classification number: F01D5/141 ,  F01D5/142 ,  F02C7/05 ,  F02C7/36 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/303 ,  F05D2260/94

    Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.

Patent Agency Ranking