利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

102 条记录 (耗时 0.009 秒)

    Systems and methods for passively directing aircraft engine nozzle flows
    32.
    发明公开
    Systems and methods for passively directing aircraft engine nozzle flows 有权
    对于被动控制飞机发动机的喷嘴流量的系统和方法

    公开(公告)号：EP1936172A3

    公开(公告)日：2010-04-21

    申请号：EP07122560.1

    申请日：2007-12-06

    申请人： The Boeing Company

    发明人： Birch, Stanley F. ,  Lyubimov, Dmitriy A. ,  Maslov, Vladimir P. ,  Secundov, Alexandr N. ,  Khritov, Konstantin M. ,  Mironov, Aleksey K.

    IPC分类号： F02K1/38 ,  F02K1/34 ,  F02K1/50

    CPC分类号： F02K1/34 ,  B64D29/02 ,  B64D33/04 ,  F02K1/30 ,  F02K1/386 ,  F05D2250/13 ,  F05D2270/173 ,  Y02T50/672

    摘要： Systems and methods for passively directing aircraft engine nozzle flow are disclosed. One system includes an aircraft nozzle attachable to an aircraft turbofan engine, with the nozzle including a first flow path wall bounding a first flow path and being positioned to receive engine exhaust products, and a second flow path wall bounding a second flow path and being positioned to receive engine bypass air. The first flow path wall is positioned between the first and second flow paths, and the second flow path wall is positioned between the second flow path and an ambient air flow path. Multiple flow passages can be positioned in at least one of the first and second flow path walls to passively direct gas from a corresponding flow path within the flow path wall through the flow path wall to a corresponding flow path external to the flow path wall. Neighboring flow passages can have neighboring circumferentially-extending and circumferentially-spaced exit openings positioned at an interface with the corresponding flow path external to the flow path wall.

    Turbine airfoil with tapered trailing edge ribs
    36.
    发明公开
    Turbine airfoil with tapered trailing edge ribs 审中-公开
    Tippinenblatt mitverjüngtenRippen an derAbströmkante

    公开(公告)号：EP1726781A1

    公开(公告)日：2006-11-29

    申请号：EP06251686.9

    申请日：2006-03-28

    申请人： The General Electric Company

    发明人： Lee, Ching-Pang ,  Brassfield, Steven Robert ,  Danowski, Michael Joseph ,  Singh, Hardev

    IPC分类号： F01D5/18

    CPC分类号： F01D5/186 ,  F01D5/187 ,  F05D2250/13 ,  F05D2250/184 ,  F05D2250/292 ,  F05D2260/221 ,  Y02T50/673 ,  Y02T50/676

    摘要： An airfoil (118) for a gas turbine engine has opposed pressure and suction sidewalls (120), (122) extending between a leading edge (124) and a trailing edge (126). The airfoil includes an array of radially-spaced apart longitudinally-extending lands (130) which define a plurality of trailing edge slots (128) therebetween. Each of the trailing edge slots (128) has an inlet in fluid communication with an interior of the airfoil (118) and an exit (134) in fluid communication with the trailing edge (126). At least one of the lands (130) is tapered such that a width of the land (130) measured in a radial direction decreases from the suction sidewall (122) to the pressure sidewall (120).

    摘要翻译： 用于燃气涡轮发动机的翼型件（118）具有在前缘（124）和后缘（126）之间延伸的相对的压力和吸力侧壁（120），（122）。 翼型件包括沿径向间隔开的纵向延伸的平台（130）的阵列，其在它们之间限定多个后缘槽（128）。 每个后缘槽（128）具有与翼型件（118）的内部和与后缘（126）流体连通的出口（134）流体连通的入口。 所述焊盘（130）中的至少一个是锥形的，使得沿径向测量的焊盘（130）的宽度从抽吸侧壁（122）减小到压力侧壁（120）。

    Gas turbine blade shroud
    37.
    发明公开
    Gas turbine blade shroud 审中-公开
    Deckbandfüreine Gasturbinenschaufel

    公开(公告)号：EP1591625A1

    公开(公告)日：2005-11-02

    申请号：EP04101875.5

    申请日：2004-04-30

    申请人： Alstom Technology Ltd

    发明人： Anguisola, McFeat, Jose Ma ,  SCHULZ, Ingolf ,  WILHELM, Dirk

    IPC分类号： F01D5/14 ,  F01D5/20 ,  F01D5/22

    CPC分类号： F01D5/141 ,  B33Y80/00 ,  F01D5/225 ,  F05D2230/90 ,  F05D2240/80 ,  F05D2250/12 ,  F05D2250/13 ,  F05D2250/141

    摘要： According to the invention a gas turbine blade shroud (4) comprises a platform (5) and one or more fins (6,7) extending toward a stator and side rails (8) that extend radially toward the stator and along the edge of the platform (5). The increased wall thickness in the side regions of the blade shroud (4) effects an increase in stiffness and a decrease in deformation during turbine operation. Due to the localised increase in wall thickness the mass of the blade shroud (4) is still minimised such that mechanical loading is not significantly increased. The side rails (8) furthermore improve the lining up of adjacent blades and decrease of the probability of hot gas leakage into the cavity between blade shroud (4) and stator. The side rails (8) have profile shapes that are optimised in view of stiffness and mechanical loading and are suitable for casting. The blade shroud (4) with side rails (8) according to the invention has improved life time.

    摘要翻译： 燃气轮机叶片护罩包括平台和朝向定子延伸的一个或多个翅片和沿着定子并沿着平台的边缘径向延伸的侧轨。 在叶片护罩的侧部区域中增加的壁厚在涡轮机操作期间增加刚度和变形减小。 由于壁厚的局部增加，叶片护罩的质量可以最小化，使得机械负载不会显着增加。 侧轨可以改善相邻叶片的排列，并降低热气体泄漏到叶片护罩和定子之间的空腔的可能性。 侧轨具有可根据刚度和机械载荷优化的轮廓形状，并且适合于铸造。 具有侧轨的叶片护罩可以具有改善的寿命。

    GAS TURBINE BLADE SHROUD
    38.
    发明授权
    GAS TURBINE BLADE SHROUD 有权

    公开(公告)号：EP1759089B1

    公开(公告)日：2018-08-08

    申请号：EP05736045.5

    申请日：2005-04-19

    申请人： Ansaldo Energia IP UK Limited

    发明人： ANGUISOLA, MCFEAT, Jose ,  SCHULZ, Ingolf ,  WILHELM, Dirk

    IPC分类号： F01D5/14 ,  F01D5/20 ,  F01D5/22

    CPC分类号： F01D5/141 ,  B33Y80/00 ,  F01D5/225 ,  F05D2230/90 ,  F05D2240/80 ,  F05D2250/12 ,  F05D2250/13 ,  F05D2250/141

    摘要： A gas turbine blade shroud includes a platform and one or more fins extending toward a stator and side rails that extend radially toward the stator and along the edge of the platform. The increased wall thickness in the side regions of the blade shroud effects an increase in stiffness and a decrease in deformation during turbine operation. Due to a localised increase in wall thickness the mass of the blade shroud can be minimized such that mechanical loading is not significantly increased. The side rails can improve a lining up of adjacent blades and decrease a probability of hot gas leakage into the cavity between blade shroud and stator. The side rails have profile shapes that can be optimised in view of stiffness and mechanical loading and are suitable for casting. The blade shroud with side rails can have an improved life time.

    VARIABLE-GEOMETRY CONVERGENT-DIVERGENT EXHAUST NOZZLE FOR A JET ENGINE AND METHOD FOR VARYING THE NOZZLE
    39.
    发明公开
    VARIABLE-GEOMETRY CONVERGENT-DIVERGENT EXHAUST NOZZLE FOR A JET ENGINE AND METHOD FOR VARYING THE NOZZLE 审中-公开
    收敛扩散形排气喷管变几何用于改变射流喷气发动机和方法

    公开(公告)号：EP3008320A4

    公开(公告)日：2017-02-22

    申请号：EP13886677

    申请日：2013-06-14

    申请人： SAAB AB

    发明人： RÄF MARTIN

    IPC分类号： F02K1/12 ,  F02K1/80

    CPC分类号： F02K1/805 ,  F02K1/1223 ,  F05D2250/11 ,  F05D2250/12 ,  F05D2250/121 ,  F05D2250/13 ,  F05D2250/132 ,  F05D2250/141 ,  F05D2260/96

    摘要： The present invention relates to a variable convergent-divergent exhaust nozzle (14) for a jet engine (1) comprising a fixed structure (16), a first cross sectional area (Al), a second cross sectional area (A2), a plurality of first flap means (18) being pivotally connectable to the fixed structure (16), a plurality of second flap means (18') being pivotally connected to the plurality of first flap means (18), first actuator means (20, 20h, 24) being arranged to actuate said first flap means (18) for variation of the nozzles (14) first cross sectional area (Al) between a first position and a second position, and second actuator means (20', 20 'h, 24') being arranged to actuate said second flap means (18') for variation of the nozzles (14) second cross sectional area (A2) between a first position and a second position. The respective first flap means (18, 24, 26) comprises third flap means (24) and fourth flap means (26), each comprising a first sliding surface (22, 22') arranged in continuous contact with adjacent first flap means (18) during said variation. The respective second flap means (18') comprises fifth flap means (24') and sixth flap means (26'), each comprising a second sliding surface (22''', 22''''') arranged in continuous contact with adjacent second flap means (18') during said variation. The present invention also relates to method for varying a variable convergent-divergent exhaust nozzle (14) for a jet engine (1).

    VARIABLE EXHAUST NOZZLE FOR A JET ENGINE AND METHOD FOR VARYING THE NOZZLE
    40.
    发明公开
    VARIABLE EXHAUST NOZZLE FOR A JET ENGINE AND METHOD FOR VARYING THE NOZZLE 审中-公开
    CHANGING排气喷管喷气发动机和方法用于改变JET

    公开(公告)号：EP3008321A4

    公开(公告)日：2017-02-15

    申请号：EP13886804

    申请日：2013-06-14

    申请人： SAAB AB

    发明人： BJERKEMO JACOB

    IPC分类号： F02K1/12

    CPC分类号： F02K1/805 ,  F02K1/1223 ,  F05D2250/12 ,  F05D2250/13 ,  F05D2250/132 ,  F05D2250/141 ,  F05D2260/96

    摘要： The present invention relates to a variable exhaust nozzle (14) for a jet engine (1), the nozzle (14) comprises an upstream portion (16), flap means (18) being pivotally connectable to the jet engine (1) via the upstream portion (16), the flap means (18) com- prises a downstream portion (16´) forming a downstream linear edge (19'), actuator means (20, 20h, 24) being arranged to actuate said flap means (18) for variation of the nozzles (14) cross sectional area (A1, A2) between a first position and a second position. Said flap means (18) is skewed. The nozzle (14) comprises shape forming flap means (24, 62) for forming the cross sectional area (A1, A2), and adjacent flap means (24, 26, 27, 28) having sliding surfaces (22, 22') in continuous contact during said variation. The present invention also relates to method for varying a variable exhaust nozzle (14) for a jet engine (1).

    摘要翻译： 本发明涉及一种可变排气喷嘴（14），用于喷气发动机（1），喷嘴（14）上游部分的方法包括：（16），翼片装置（18）枢转地连接到经由喷气发动机（1） 上游部分（16），所述翼片装置（18）的COM prises '形成下游直线边缘（19）的下游部分（16）'，致动器装置（20，20H，24）被布置成致动所述翼片装置（18 ），用于在第一位置和第二位置之间的喷嘴（14）的横截面面积（A1，A2）的变化。 所述翼片装置（18）是倾斜的。 喷嘴（14）包括形状成形挡板形成的横截面面积（A1，A2）的装置（24，62），和相邻翼片装置（24，26，27，28）具有滑动面（22，22“）在 所述变化期间连续接触。 因此，本发明涉及一种用于为一个喷气发动机（1）变化的可变排气喷嘴（14）。