An airfoil assembly has at least one cooling hole in an aft edge of at least one platform for cooling at least one of an axially downstream airfoil root and/or tip region. The airfoil assembly may be a high pressure turbine first stage vane coupled with a combustor operating at a low Pattern Factor.
申请公布号
WO2015147930(A3)
申请公布日期
2015.11.26
申请号
WO2014US71582
申请日期
2014.12.19
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
CHAKKA, PITCHAIAH VIJAY;AGGARWALA, ANDREW S.;PRAISNER, THOMAS J.;SPANGLER, BRANDON W.
