INTERNALLY COOLED AIRFOIL FOR A GAS TURBINE ENGINE AND METHOD
摘要
An internally-cooled airfoil for a gas turbine engine, wherein the airfoil comprises at least one substantially chordwise-extending and internally-projecting stiffener located on an internal surface of one of the sidewalls and adjacent to the insert.
申请公布号
CA2528724(C)
申请公布日期
2011.01.25
申请号
CA20052528724
申请日期
2005.11.28
申请人
PRATT & WHITNEY CANADA CORP.
发明人
TRINDADE, RICARDO;DJERIDANE, TOUFIK;SREEKANTH, SRI;PAPPLE, MICHAEL
