Effects of mistuning on bending-torsion flutter and response of a cascade in incompressible flow
An investigation of the effects of blade mistuning on the aeroelastic stability and response of a cascade in incompressible flow is reported. The aerodynamic, inertial, and structural coupling between the bending and torsional motions of each blade and the aerodynamic coupling between the blades are included in the formulation. A digital computer program was developed to conduct parametric studies. Results indicate that the mistuning has a beneficial effect on the coupled bending-torsion and uncoupled torsion flutter. The effect of mistuning on forced response, however, may be either beneficial or adverse, depending on the engine order of the forcing function. Additionally, the results illustrate that it may be feasible to utilize mistuning as a passive control to increase flutter speed while maintaining forced response at an acceptable level.
- Research Organization:
- Toledo Univ., OH (USA); National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
- DOE Contract Number:
- AI01-76ET20320
- OSTI ID:
- 6937841
- Report Number(s):
- DOE/NASA/1028-29; NASA-TM-81674; CONF-810401-2
- Country of Publication:
- United States
- Language:
- English
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