| 摘要 |
<p>A tip cap (22), (32), (44), (52), (62), (70) for a fan blade (8) of a gas turbine engine comprises: a tip portion (24); and an insert portion (26), (34), (46), (54), (64), (72) arranged to be received in a recess (20) of an aerofoil (10) of a fan blade (8), wherein the insert portion comprises regions of different density. An alternative fan blade 8 for a gas turbine engine comprises: an aerofoil (10) having a tip recess (20) for receiving an insert portion of a tip cap; a tip cap (22), (32), (44), (52), (62), (70) having a tip portion (24) and an insert portion (26), ((34), 46), (54), (64), (72), the insert portion having at least one cut-out (28), (36), (38), (48), (80); wherein the insert portion of the tip cap is disposed within the tip recess of the aerofoil, and wherein a void is defined by the cut-out within the recess.</p> |
