A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a maximum chord length projection that is not in an axial view.
申请公布号
WO2015175073(A3)
申请公布日期
2016.01.14
申请号
WO2015US16584
申请日期
2015.02.19
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
GALLAGHER, EDWARD J.;MONZON, BYRON R.;LIU, LING;LI, LINDA S.;WHITLOW, DARRYL;FORD, BARRY M.