DUCTED PROPULSOR WITH AIRFOILS HAVING A LEADING EDGE WITH A DEFLECTED REGION

摘要

The present invention relates to gas turbine engines (10) comprising a turbofan (12) having a plurality of fan blades (131). Each fan blade (131) comprises a leading edge (133) and a leading edge zone (135) immediately downstream the leading edge (133). The leading edge zone (135) extends in a spanwise direction over the full length of the fan blade (131). The leading edge zone (135) comprises one or more deflected regions (145) forming a depression with a depth tapering in chordal direction so as to blend with the main body (137). The deflected regions (145) locally reduce the angle of attack between non-deflected regions (147). The deflected regions (145) extend from the leading edge (133) to between 1 % and 50%, more preferably between 5% and 25%, of the chordal extent of the fan blade (131). Thus, flow separation is mitigated reducing broadband noise and overall lift loss and drag.