FAN BLADE TALL DOVETAIL FOR INDIVIDUALLY BLADED ROTORS
摘要
A fan blade for a gas turbine engine includes an airfoil that defines a pressure and suction side. A neck supports the airfoil and interconnects to a dovetail by opposing radii. The dovetail includes a bearing surface tangent to one of the radii at a tangent point. The dovetail has a dovetail width and a vertical bearing surface height from the tangent point to a bottom of the dovetail opposite the neck. A first ratio of the dovetail width to the vertical bearing surface height is in a range of substantially between 2.32 to 2.90.
申请公布号
WO2014046735(A1)
申请公布日期
2014.03.27
申请号
WO2013US31868
申请日期
2013.03.15
申请人
UNITED TECHNOLOGIES CORPORATION;WHITEHURST, SEAN A.;MCCOMB, PATRICK JAMES;DROZDENKO, LEE
发明人
WHITEHURST, SEAN A.;MCCOMB, PATRICK JAMES;DROZDENKO, LEE