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    GAS TURBINE BLADE SHROUD
    1.
    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
    3.
    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
    4.
    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）。

    BEC DE SÉPARATION DE COMPRESSEUR BASSE PRESSION DE TURBOMACHINE AXIALE AVEC CONDUIT ANNULAIRE DE DÉGIVRAGE
    6.
    发明公开
    BEC DE SÉPARATION DE COMPRESSEUR BASSE PRESSION DE TURBOMACHINE AXIALE AVEC CONDUIT ANNULAIRE DE DÉGIVRAGE 有权
    美国爱丁堡NIEDERDRUCKKOMPRESSORS EINER AXIALEN TURBOMASCHINE MITRINGFÖRMIGERENTEISUNGSLEITUNG

    公开(公告)号：EP3118423A1

    公开(公告)日：2017-01-18

    申请号：EP16177541.6

    申请日：2016-07-01

    申请人： Safran Aero Boosters SA

    发明人： CORTEQUISSE, Jean-François

    IPC分类号： F01D25/02 ,  F02C7/047 ,  F04D29/58

    CPC分类号： F01D25/02 ,  B64D33/02 ,  B64D2033/0233 ,  F02C7/047 ,  F04D29/522 ,  F04D29/542 ,  F04D29/545 ,  F04D29/584 ,  F05D2220/323 ,  F05D2250/141 ,  F05D2260/30

    摘要： L'invention consiste en un bec de séparation (17) de turbomachine axiale, notamment de compresseur (4), ledit bec comprenant : une enveloppe annulaire (30) un conduit annulaire (34) pour le dégivrage d'un bord de séparation (22) du bec ; le conduit (34) est lié à l'enveloppe (30) uniquement à une première zone (42) au niveau d'une entrée d'air chaud (36) et à une deuxième zone (64) située à une position diamétralement opposée à ladite entrée ou formant par rapport à l'axe (14) de la turbomachine un angle ( α ) de moins de 30° avec ladite position, de manière à permettre des déformations de dilatation du conduit. L'invention consiste également en un compresseur (4) et une turbomachine comprenant un tel bec de séparation (17).

    摘要翻译： 本发明包括轴向涡轮机的分流器鼻部，特别是压缩机，分离器鼻部包括：环形壳体，用于使分流器鼻部的分离边缘除冰的环形导管; 导管仅在热空气入口的区域中的第一区域和位于与入口直径相对的位置的第二区域中连接到壳体，或者相对于涡轮机的轴线形成小于30°的角度α 相对于该位置，以允许导管的膨胀变形。 本发明还包括压缩机和包括这种分流器鼻部的涡轮机。

    COOLED AIRFOIL TRAILING EDGE AND METHOD OF COOLING THE AIRFOIL TRAILING EDGE
    9.
    发明公开
    COOLED AIRFOIL TRAILING EDGE AND METHOD OF COOLING THE AIRFOIL TRAILING EDGE 审中-公开
    GEKÜHLTETRAGFLÄCHENHINTERKANTEUND VERFAHREN ZURKÜHLUNGDERTRAGFLÄCHENHINTERKANTE

    公开(公告)号：EP3074604A2

    公开(公告)日：2016-10-05

    申请号：EP14868713.0

    申请日：2014-11-21

    申请人： General Electric Company

    发明人： WANG, Guanghua ,  BUNKER, Ronald, Scott ,  BAILEY, Jeremy, Clyde ,  DELANCEY, James, Peter ,  HELMER, David, Benjamin

    IPC分类号： F01D5/18 ,  F01D9/04 ,  F01D9/06

    CPC分类号： F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D9/065 ,  F05D2240/304 ,  F05D2250/13 ,  F05D2250/131 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/324 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676

    摘要： An airfoil and method of cooling a airfoil including a leading edge, a trailing edge, a suction side, a pressure side and at least one internal cooling channel configured to convey a cooling fluid, is provided. A plurality of trailing edge bleed slots are in fluid communication with the at least one internal cooling channel, wherein a downstream edge of the pressure side of the airfoil lies upstream of a downstream edge of the suction side to expose the plurality of trailing edge bleed slots proximate to the trailing edge of the airfoil. The at least one internal cooling channel is configured to supply the cooling fluid from a source of cooling fluid towards the plurality of trailing edge bleed slots. A plurality of obstruction features are disposed within the at least one internal cooling channel and at a downstream edge of the remaining pressure side. The one or more obstruction features are configured having a predefined substantially polygon shape, to distribute a flow of the cooling fluid and provide distributed cooling to the plurality of trailing edge bleed slots.

    摘要翻译： 提供了一种用于冷却包括前缘，后缘，吸力侧，压力侧和构造成输送冷却流体的至少一个内部冷却通道的翼型的翼型件和方法。 多个后缘排出槽与至少一个内部冷却通道流体连通，其中翼型的压力侧的下游边缘位于吸力侧的下游边缘的上游，以暴露多个后缘排放槽 靠近翼型的后缘。 至少一个内部冷却通道构造成将冷却流体从冷却流体源向多个后缘排放槽供应。 多个阻塞特征设置在至少一个内部冷却通道内和在剩余压力侧的下游边缘处。 一个或多个障碍物特征被构造成具有预定的基本上多边形的形状，以分配冷却流体的流动并且向多个后缘排放槽提供分布式冷却。