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    14.
    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.

    15.
    发明专利
    未知

    公开(公告)号：DE602004023769D1

    公开(公告)日：2009-12-03

    申请号：DE602004023769

    申请日：2004-12-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  ROBERGE GARY D ,  MERRY BRIAN

    IPC: F01D5/34 ,  F01D5/02 ,  F01D5/06 ,  F02C3/073 ,  F02K3/068

    Abstract: Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially therefrom. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.

    16.
    发明专利
    未知

    公开(公告)号：DE60027650T2

    公开(公告)日：2006-09-14

    申请号：DE60027650

    申请日：2000-08-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZELESKY MARK F ,  STEUBER GARY D ,  KANE DANIEL E ,  MERRY BRIAN

    IPC: F01D5/18 ,  F01D9/02 ,  F01D9/04

    Abstract: A coolable stator vane 46 having a platform 48, 54 having internal cooling for the platform is disclosed. Various construction details are developed for cooling the interior of the platform in the trailing edge region 126, 146 of the platform. In one particular embodiment, the platform has a two-pass passage 168 in flow communication with the exterior of the platform, the rearmost pass 170 discharging more than half the cooling fluid entering the two pass passage.

    17.
    发明专利
    未知

    公开(公告)号：DE60027650D1

    公开(公告)日：2006-06-08

    申请号：DE60027650

    申请日：2000-08-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ZELESKY MARK F ,  STEUBER GARY D ,  KANE DANIEL E ,  MERRY BRIAN

    IPC: F01D5/18 ,  F01D9/02 ,  F01D9/04

    Abstract: A coolable stator vane 46 having a platform 48, 54 having internal cooling for the platform is disclosed. Various construction details are developed for cooling the interior of the platform in the trailing edge region 126, 146 of the platform. In one particular embodiment, the platform has a two-pass passage 168 in flow communication with the exterior of the platform, the rearmost pass 170 discharging more than half the cooling fluid entering the two pass passage.

    19.
    发明专利
    未知

    公开(公告)号：DE602004019709D1

    公开(公告)日：2009-04-09

    申请号：DE602004019709

    申请日：2004-12-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  NORRIS JAMES W ,  NORDEEN CRAIG A ,  MERRY BRIAN

    IPC: F02C3/073 ,  F02K3/068 ,  F23R3/52

    Abstract: A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining compressor chambers extending radially therein. A turbine is mounted to the outer periphery of the fan. A diffuser at a radially outer end of each compressor chamber turns core airflow through the compressor chamber toward the combustor. The high velocity, high pressure core airflow from the compressor chambers in the hollow fan blades is diffused before the compressed core airflow enters the combustor, thereby improving the efficiency of the tip turbine engine. Further, the overall diameter of the tip turbine engine is reduced by the arrangement of the diffuser case in a position not directly radially outward of the fan blades.

    20.
    发明专利
    未知

    公开(公告)号：DE60032419T2

    公开(公告)日：2007-05-16

    申请号：DE60032419

    申请日：2000-08-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MERRY BRIAN

    IPC: F01D5/18 ,  F01D9/02 ,  F01D11/00

    Abstract: A method for cooling the trailing edge 126, 146 region of a stator vane platform 48, 54 and for forming a cooling passage 198, 214 using platform slots in the side of a stator vane is disclosed. Various steps are developed which provide for effective cooling with minimal intrusion into the working medium flowpath 18. In one particular embodiment, the method includes extending a feather seal slot rearwardly with an extension 88, 96 in facing sides 116, 118, or 136, 138 of a pair of vane platforms 48, 54 and for flowing cooling fluid laterally prior to discharging the cooling air for impingement cooling of an adjacent stator vane.

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