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    Cooled rotor blade with vibration damping device
    15.
    发明专利
    Cooled rotor blade with vibration damping device 未知

    公开(公告)号：AU2004240221A1

    公开(公告)日：2005-07-07

    申请号：AU2004240221

    申请日：2004-12-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MONGILLO DOMINIC J JR ,  GREGG SHAWN J

    IPC: F01D5/16 ,  F01D5/18 ,  F02C7/24

    Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (180, an airfoil (20), and a damper (24). The airfoil (20) includes a base (28), a tip (30), a pressure side wall (36), a suction side wall (38), and a cavity (40) disposed therebetween. The cavity (40) extends substantially between the base (28) and the tip (30), and includes a first cavity portion (44), a second cavity portion (46), and a channel (42) disposed between the first cavity portion (44) and the second cavity portion (46). A plurality of first pedestals (48) are disposed within the first cavity portion (44) adjacent the channel (42), and a plurality of second pedestals (48) are disposed within the second cavity portion (46) adjacent the channel (42). The damper (24) is selectively received within the channel (42).

    COOLED ROTOR BLADE WITH VIBRATION DAMPING DEVICE
    16.
    发明专利
    COOLED ROTOR BLADE WITH VIBRATION DAMPING DEVICE 未知

    公开(公告)号：CA2486988A1

    公开(公告)日：2005-06-19

    申请号：CA2486988

    申请日：2004-11-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MONGILLO DOMINIC J JR ,  GREGG SHAWN J

    IPC: F01D5/16 ,  F01D5/18

    Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a roo t (18), an airfoil (20), and a damper (24). The airfoil (20) includes a base (28), a ti p (30), a pressure side wall (36), a suction side wall (38), and a cavity (40) disposed therebetween. The cavity (40) extends substantially between the base (28) and the tip (30), an d includes a first cavity portion (44), a second cavity portion (46), and a channel (42) dispos ed between the first cavity portion (44) and the second cavity portion (46). A plurality of first pedestals (48) are disposed within the first cavity portion (44) adjacent the channel (42), and a plurality of second pedestals (48) are disposed within the second cavity portion (46) adjacent the channel (42). The damper (24) is selectively received within th e channel (42).

    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE WITH CHEVRONS
    19.
    发明公开
    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE WITH CHEVRONS 审中-公开
    舒兰菲尔德KÜHLKANALMIT WINKELLEISTENFÜREINEN GASTURBINENMOTOR

    公开(公告)号：EP2938830A4

    公开(公告)日：2016-08-17

    申请号：EP13869557

    申请日：2013-12-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： GOELLER TRAVIS ,  GRANSTRAND ERIK R ,  SINGER IRWIN D ,  MONGILLO DOMINIC J JR ,  PIETRASZKIEWICZ EDWARD F

    IPC: F01D5/18

    CPC classification number: F01D5/188 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing.

    Abstract translation: 燃气涡轮发动机部件包括具有冷却通道的结构，所述冷却通道提供通过内壁彼此分离并通过弯曲部流体连接的上游和下游部分。 第一和第二跳闸条分别布置在上游和下游部分中。 第一行程条以彼此之间的第一间距布置。 第二跳闸条以相互间隔开的第二间隔布置。 湍流促进器被布置在弯曲中并且与第一跳闸条的第三间隔相比第一间隔不同。 湍流促进器布置在与第二间隔不同的第二跳闸带的第四间隔处。

    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION
    20.
    发明公开
    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION 审中-公开
    HINTERKANTEN- ODER SPITZENFLAGGEN-FLUSSTRENNUNG

    公开(公告)号：EP2828485A4

    公开(公告)日：2016-07-27

    申请号：EP13763814

    申请日：2013-01-10

    Applicant: UNITED TECHNOLOGIES CORP ,  GAUTSCHI STEVEN BRUCE ,  SPANGLER BRANDON W ,  QUACH SAN ,  MONGILLO DOMINIC J JR

    Inventor： GAUTSCHI STEVEN BRUCE ,  SPANGLER BRANDON W ,  QUACH SAN ,  MONGILLO DOMINIC J JR

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F05D2240/122 ,  F05D2240/125 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2250/314 ,  F05D2250/324 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil. The cooling passageway is located within the central cavity at the trailing edge region. The column of flow separators is located in the cooling passageway adjacent the trailing edge and includes a first flow separator having a first longitudinal axis and a second flow separator having a second longitudinal axis. The first longitudinal axis is offset at an angle with respect to the first longitudinal axis.

    Abstract translation: 翼型件包括前缘，后缘区域，吸力表面，压力表面，冷却通道和流动分离器柱。 吸力表面和压力表面两者都在前缘和后缘区域之间轴向延伸，并且从翼型的根部径向延伸到翼型的尖端部分，以限定翼型的中心空腔。 冷却通道位于后缘区域的中心腔内。 流动分离器的柱位于与后缘相邻的冷却通道中，并且包括具有第一纵向轴线的第一流动分离器和具有第二纵向轴线的第二流动分离器。 第一纵向轴线相对于第一纵向轴线以一定角度偏移。

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