Patent ID: 8784042

Claim:
Fan downstream guide vanes for a turbofan engine, comprising: the downstream guide vanes extending in one vane height between an inner and an outer sidewall in a bypass duct of the turbofan engine and whose shape is established by a plurality of aerodynamic profiles radially stacked on top of each other and determined by a skeleton line angle distribution with an appertaining, superimposed thickness distribution over a chord length an upper and a lower profile ( 1 max , 2 min ) forming an upper limitation and a lower limitation determined by specified supporting points (St) of chord lengths of 0, 9, 14, 22, 35, 46, 60, 89 and 100%, respectively having: dimensionless values of a skeleton line angle (αl o ) of 0, 0.2, 0.4, 0.6, 0.8, 0.9, 0.9, 0.95 and 1 and a thickness (d o ) of 0, 0.85, 0.95, 1, 0.95, 0.875, 0.7, 0.2 and 0 as the upper limitation of a skeleton line angle distribution and a thickness distribution ( 1 Smax , 1 Dmax ); a skeleton line angle (αl u ) of 0, 0.05, 0.1, 0.25, 0.45, 0.6, 0.725, 0.85 and 1 and a thickness (d u ) of 0, 0.4, 0.55, 0.75, 0.95, 1, 0.9, 0.35, and 0 as the lower limitation of the skeleton line angle distribution and the thickness distribution ( 2 Smax , 2 Dmax ); and a plurality of intermediate profiles ( 3 int ) situated between the upper and the lower limitations.