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Optimal Design and Acoustic Assessment of Low-Vibration Rotor Blades


Affiliations
1 Department of Engineering, Roma Tre University, 00146 Rome, Italy
2 Department of Mechanical, Materials and Manufacturing Engineering, The University of Nottingham, Nottingham NG7 2RD, United Kingdom
 

An optimal procedure for the design of rotor blade that generates low vibratory hub loads in nonaxial flow conditions is presented and applied to a helicopter rotor in forward flight, a condition where vibrations and noise become severe. Blade shape and structural properties are the design parameters to be identified within a binary genetic optimization algorithm under aeroelastic stability constraint. The process exploits an aeroelastic solver that is based on a nonlinear, beam-likemodel, suited for the analysis of arbitrary curved-elastic-axis blades, with the introduction of a surrogate wake inflow model for the analysis of sectional aerodynamic loads. Numerical results are presented to demonstrate the capability of the proposed approach to identify low vibratory hub loads rotor blades as well as to assess the robustness of solution at off-design operating conditions. Further, the aeroacoustic assessment of the rotor configurations determined is carried out in order to examine the impact of low-vibration blade design on the emitted noise field.
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  • Optimal Design and Acoustic Assessment of Low-Vibration Rotor Blades

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Authors

G. Bernardini
Department of Engineering, Roma Tre University, 00146 Rome, Italy
E. Piccione
Department of Engineering, Roma Tre University, 00146 Rome, Italy
A. Anobile
Department of Mechanical, Materials and Manufacturing Engineering, The University of Nottingham, Nottingham NG7 2RD, United Kingdom
J. Serafini
Department of Engineering, Roma Tre University, 00146 Rome, Italy
M. Gennaretti
Department of Engineering, Roma Tre University, 00146 Rome, Italy

Abstract


An optimal procedure for the design of rotor blade that generates low vibratory hub loads in nonaxial flow conditions is presented and applied to a helicopter rotor in forward flight, a condition where vibrations and noise become severe. Blade shape and structural properties are the design parameters to be identified within a binary genetic optimization algorithm under aeroelastic stability constraint. The process exploits an aeroelastic solver that is based on a nonlinear, beam-likemodel, suited for the analysis of arbitrary curved-elastic-axis blades, with the introduction of a surrogate wake inflow model for the analysis of sectional aerodynamic loads. Numerical results are presented to demonstrate the capability of the proposed approach to identify low vibratory hub loads rotor blades as well as to assess the robustness of solution at off-design operating conditions. Further, the aeroacoustic assessment of the rotor configurations determined is carried out in order to examine the impact of low-vibration blade design on the emitted noise field.