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investigation of the Effect of Piezo-Electric Patch on the Modal Properties and Flutter Speed of Turbomachine Blade

Yousefi, Masoud | 2017

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 50380 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Haddadpour, Hassan
  7. Abstract:
  8. In order to investigaton of dynamics behavior and determination of the aeroelastic stability of the turbomachine blade. the turbomachine blade is modeled by using the beam model, taking into account all degrees of freedom, the effect of warping, rotation and seting angle. For aerodynamic modeling, the Smith and Whitehead models are used which are valid in subsonic flow. The validity of the derived formulation is confirmed through comparison with those obtained from the finite element software and the available results in the literature. Then, by using the state feedback controller, the effect of sensor and piezoelectric actuator on the vibrations reduction of the structure and increasing the aeroelastic stability range is considered. Various parametric studies including the effects of rotating speed and setting angle are examined for the considered configuration of the rotating blade. The results show that the natural frequency of the rotating blade of a turbomachinery is strongly influenced by hub radius and setting angle. Also results show that by using acceptable control gain the amplitude of vibration is decreased and the aeroelastic stability margin is increased
  9. Keywords:
  10. Aeroelasticity ; Smart Structures ; Whitehead Group ; Piezoelectric Patches ; Turbomachines ; Smart Structures ; Smith Model

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