公开(公告)号：SG11201402892VA

公开(公告)日：2014-10-30

申请号：SG11201402892V

申请日：2012-12-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MERRY BRIAN ,  SUCIU GABRIEL L ,  NORRIS JAMES W ,  SIRICA STEVEN J ,  SCHWARZ FREDERICK M

IPC: F02K3/02 ,  F02C3/04 ,  F02C3/073

Abstract: A turbine engine includes a compressor section, a combustor arranged in fluid-receiving communication with the compressor section, a turbine section arranged in fluid-receiving communication with the combustor and a gearbox assembly coupled to be driven by the turbine section. The gearbox assembly is located at an axial position that is aft of the compressor section.

公开(公告)号：DE602004031986D1

公开(公告)日：2011-05-05

申请号：DE602004031986

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

公开(公告)号：DE602004019710D1

公开(公告)日：2009-04-09

申请号：DE602004019710

申请日：2004-12-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SUCIU GABRIEL L ,  MERRY BRIAN

IPC: F02K3/02 ,  F01D17/16 ,  F02C7/057

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.

公开(公告)号：DE60032419D1

公开(公告)日：2007-02-01

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.

公开(公告)号：EP2798186A4

公开(公告)日：2015-08-12

申请号：EP12863020

申请日：2012-12-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MERRY BRIAN ,  SUCIU GABRIEL L ,  NORRIS JAMES W ,  SIRICA STEVEN J ,  SCHWARZ FREDERICK M

IPC: F02K3/02 ,  F01D17/16 ,  F02C3/073 ,  F02C3/08 ,  F02C3/107 ,  F02C7/36 ,  F02C9/20 ,  F02K3/068

CPC classification number: F01D17/162 ,  F02C3/073 ,  F02C3/08 ,  F02C3/107 ,  F02C7/36 ,  F02C9/20 ,  F02K3/068 ,  F05D2270/02 ,  F05D2270/101 ,  F05D2270/301 ,  F05D2270/304 ,  Y02T50/671