The optimal design of the disk of a turbine engine rotor stage is examined as a means of reducing worst-case blade vibration and stress levels. The cross-sectional profile of the disk is modified in search of an optimum that achieves minimum weight while ensuring that the stresses due to centrifugal loading and vibration remain below a safe level, as defined by a Goodman diagram, even when blade mistuning is introduced. In order to predict the vibration response of a tuned or mistuned bladed disk, a reduced-order modeling technique is employed. Rotational effects are included in the reduced-order model, and a response metric based on vibration energy is used to estimate the dynamic stress level. This process enables the evaluation of a design configuration in a manner that is sufficiently rapid to enable a comprehensive design optimization process. Using two example systems, the developed design methodology is found to yield bladed disk designs that are less sensitive to blade mistuning, thus reducing maximum stress and alleviating high cycle fatigue failure concerns.

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