| 摘要 |
A gas turbine engine (20) includes a rotor (62) that has a rotor disk (66; 166; 266; 366) and a plurality of circumferentially-spaced blades (68; 168). The rotor disk (66; 166; 266; 366) and the blades are co-rotatable about an axis (A). A case (64) circumscribes the rotor. The rotor disk (66; 166; 266; 366) is tuned, with regard to centrifugal and thermal growth responsiveness, to the case for a given operational scenario of the gas turbine engine (20) such that the rotor disk (66; 166; 266; 366) and case (64) together provide a tuned clearance response. The operational scenario involves a series of engine events that include at least two of engine acceleration, engine deceleration, engine steady-state operation. |
