| 摘要 |
A rotor (22) for a gas turbine engine (10) includes a hub (28) having an outer periphery (30), a first plurality of blades (24) arranged on the outer periphery (30) of the hub (28), and a second plurality of blades (26) arranged on the outer periphery (30) of the hub (28). The first plurality of blades (24) is made of a first material (32) and has a first elastic modulus over density ratio. The first plurality of blades (24) has a first natural frequency. The second plurality of blades (26) is made of a second material (34) and has a second elastic modulus over density ratio. The second elastic modulus over density ratio is different from the first elastic modulus over density ratio. The second plurality of blades (26) has a second natural frequency different from the first natural frequency. A method of fabricating a bladed rotor is also presented. |
