| 摘要 |
PROBLEM TO BE SOLVED: To provide a composite fan blade for an aircraft gas turbine engine to reduce weight and cost.SOLUTION: A gas turbine engine airfoil 45 includes leading and trailing edges LE and TE, pressure and suction sides 41 and 43 extending from an airfoil base 49 to an airfoil tip 47, and a trailing edge cladding 46 made of a cladding material bonded to a composite core 44 made of a composite material. The cladding material is less brittle than the composite material, the composite core includes a central core part 63 extending downstream from a leading edge part 48 to a trailing edge part 50 of the composite core, and the trailing edge cladding includes a wavy wall 70 and a trailing edge. Pressure and suction side flanks of the trailing edge cladding 46 may be bonded to pressure and suction side surfaces of the trailing edge part 50. Waves 68 of the wavy wall 70 may extend normal to and away from the pressure and suction side surfaces. |
