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    AIRFOIL HAVING MINIMUM DISTANCE RIBS
    1.
    发明申请
    AIRFOIL HAVING MINIMUM DISTANCE RIBS 审中-公开
    AIRFOIL具有最小距离的RIBS

    公开(公告)号：WO2014011289A3

    公开(公告)日：2014-03-27

    申请号：PCT/US2013036510

    申请日：2013-04-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FISK BENJAMIN T ,  PROPHETER-HINCKLEY TRACY A ,  DOLANSKY GREGORY M ,  TRACY ANITA L ,  TAFFET STEVEN

    IPC: F01D5/14 ,  F02C7/00

    CPC classification number: F01D5/147 ,  B23P15/02 ,  F01D5/187 ,  F05D2260/22141 ,  Y10T29/49336

    Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.

    Abstract translation: 翼型包括限定纵向轴线的翼型体。 翼型体包括前缘和后缘以及第一侧壁和第二侧壁，第二侧壁与第一侧壁间隔开以在其间限定弧线。 第一侧壁和第二侧壁连接前缘和后缘并且至少部分地限定翼型体中的空腔。 多个肋在腔内纵向延伸并且相对于纵向轴线彼此侧向间隔开。 在垂直于纵向轴线的至少一个平面中，每个肋沿着垂直于弧线的相应最小距离方向连接第一侧壁和第二侧壁。 各个最小距离方向中的至少两个是不平行的。

    4.
    发明专利
    未知

    公开(公告)号：DE60221074T2

    公开(公告)日：2008-03-13

    申请号：DE60221074

    申请日：2002-05-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND C ,  MERRY BRIAN ,  DOLANSKY GREGORY M ,  REINHARDT GREGORY E

    IPC: B23P6/00 ,  F01D5/12 ,  B23P6/04 ,  F01D5/00 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00

    Abstract: The present invention relates to a method for repairing a turbine blade 10 having a crack 16 in a trailing edge portion 26 of the blade 10. The disclosed method comprises the steps of cutting back a first surface 18 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located, and cutting back a second surface 20 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located. Each cut back step comprises cutting back the respective surface 18,20 by a depth L greater than the length of the crack 16 and less than the trailing edge radius to remove the crack 16 and form a cut back trailing edge portion 28. A compound radius is used to prevent a blunt transition into the trailing edge 12 that would result in aerodynamic losses and to reduce the airfoil root stresses. The method also includes applying a thermal barrier coating to the turbine blade 10 to increase service life. Prior to applying the coating, the tip portion 46 of the turbine blade 10 is modified to account for the change in the thermal characteristics of the turbine blade 10.

    AIRFOIL INCLUDING DAMPER MEMBER
    5.
    发明专利
    AIRFOIL INCLUDING DAMPER MEMBER 未知

    公开(公告)号：SG11201406220RA

    公开(公告)日：2014-11-27

    申请号：SG11201406220R

    申请日：2013-04-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DOLANSKY GREGORY M ,  PROPHETER-HINCKLEY TRACY A ,  FISK BENJAMIN T

    IPC: F01D5/12 ,  F01D5/18 ,  F01D9/00 ,  F02K3/00 ,  F03C7/00

    Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is faced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity. The damper member includes a first end and a second end. The first end is connected in a first joint to the first sidewall at a first longitudinal location and the second end is connected in a second joint to the second sidewall at a second, different longitudinal location.

    6.
    发明专利
    未知

    公开(公告)号：DE60221074D1

    公开(公告)日：2007-08-23

    申请号：DE60221074

    申请日：2002-05-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SURACE RAYMOND C ,  MERRY BRIAN ,  DOLANSKY GREGORY M ,  REINHARDT GREGORY E

    IPC: B23P6/00 ,  F01D5/12 ,  B23P6/04 ,  F01D5/00 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00

    Abstract: The present invention relates to a method for repairing a turbine blade 10 having a crack 16 in a trailing edge portion 26 of the blade 10. The disclosed method comprises the steps of cutting back a first surface 18 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located, and cutting back a second surface 20 of the turbine blade 10 adjacent the blade trailing edge portion 26 where the crack 16 is located. Each cut back step comprises cutting back the respective surface 18,20 by a depth L greater than the length of the crack 16 and less than the trailing edge radius to remove the crack 16 and form a cut back trailing edge portion 28. A compound radius is used to prevent a blunt transition into the trailing edge 12 that would result in aerodynamic losses and to reduce the airfoil root stresses. The method also includes applying a thermal barrier coating to the turbine blade 10 to increase service life. Prior to applying the coating, the tip portion 46 of the turbine blade 10 is modified to account for the change in the thermal characteristics of the turbine blade 10.

    AIRFOIL HAVING MINIMUM DISTANCE RIBS
    7.
    发明公开
    AIRFOIL HAVING MINIMUM DISTANCE RIBS 审中-公开
    SCOOP最小距离是肋骨

    公开(公告)号：EP2841707A4

    公开(公告)日：2016-07-27

    申请号：EP13817461

    申请日：2013-04-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FISK BENJAMIN T ,  PROPHETER-HINCKLEY TRACY A ,  DOLANSKY GREGORY M ,  TRACY ANITA L ,  TAFFET STEVEN

    IPC: F01D5/14 ,  B23P15/02 ,  F01D5/18 ,  F02C7/00

    CPC classification number: F01D5/147 ,  B23P15/02 ,  F01D5/187 ,  F05D2260/22141 ,  Y10T29/49336

    Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.

    AIRFOIL HAVING TAPERED BUTTRESS
    10.
    发明公开
    AIRFOIL HAVING TAPERED BUTTRESS 审中-公开
    SCOOP锥形支持

    公开(公告)号：EP2841702A4

    公开(公告)日：2016-03-16

    申请号：EP13781752

    申请日：2013-04-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FISK BENJAMIN T ,  PROPHETER-HINCKLEY TRACY A ,  DOLANSKY GREGORY M ,  TRACY ANITA L

    IPC: F01D5/12 ,  F01D5/14 ,  F01D5/18 ,  F01D9/00 ,  F02C7/12 ,  F02K3/00

    CPC classification number: F01D5/147 ,  F05D2230/31

    Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first sidewall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. At least one of the first side wall and the second side wall includes at least one longitudinally elongated buttress that tapers longitudinally. The at least one longitudinally elongated buttress defines an increased thickness of, respectively, the first side wall or the second sidewall. The at least one longitudinally elongated buttress projects partially across the cavity toward the other of the first side wall or the second sidewall.

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