Journal Article

An inverse design procedure has been developed for the optimum mistuning of a high bypass ratio shroudless fan. The fan is modeled as a cascade of blades, each with a single torsional degree of freedom. Linearized supersonic aerodynamic theory is used to compute the unsteady aerodynamic forces in the influence coefficient form at a typical blade section. The mistuning pattern is then numerically optimized using the method of nonlinear programming via augmented Lagrangians. The objective of the mistuning is to achieve a specified increase in aeroelastic stability margin with a minimum amount of mistuning. It is shown that a necessary but not sufficient condition for aeroelastic stability is that the blades be self-damped.

Duke Authors

Cited Authors

  • Crawley, EF; Hall, KC

Published Date

  • 1985

Published In

  • Journal of Engineering for Gas Turbines and Power

Volume / Issue

  • 107 / 2

Start / End Page

  • 418 - 426