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Computational aeroelastic analysis of slowed rotors at high advance ratios

Published online by Cambridge University Press:  27 January 2016

J. de Montaudouin ,
N. Reveles  and
M. J. Smith
J. de Montaudouin*
Affiliation:
Daniel Guggenheim School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, Georgia, USA
N. Reveles*
Affiliation:
Daniel Guggenheim School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, Georgia, USA
M. J. Smith*
Affiliation:
Daniel Guggenheim School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, Georgia, USA
*
jean.demontaudouin@gatech.edu
Nic.reveles@gatech.edu
ms55@mail.gatech.edu
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Abstract

The aerodynamic and aeroelastic behaviour of a rotor become more complex as advance ratios increase to achieve high-speed forward fight. As the rotor blades encounter large regions of cross and reverse flows during each revolution, strong variations in the local Mach regime are encountered, inducing complex elastic blade deformations. In addition, the wake system may remain in the vicinity of the rotor, adding complexity to the blade loading. The aeroelastic behaviour of a model rotor with advance ratios ranging from 0·5 to 2·0 has been evaluated with aerodynamics provided via a computational fluid dynamics (CFD) method. Significant radial blade-vortex interaction can occur at a high advance ratio; the advance ratio at which this occurs is dependent on the rotor configuration. This condition is accompanied by high vibratory loads, peak negative torsion, and peak torsion and in-plane loads. The high vibratory loading increases the sensitivity of the trim model, so that at some high advance ratios the vibratory loads must be filtered to achieve a trimmed state.

Type
Research Article
Information
The Aeronautical Journal , Volume 118 , Issue 1201 , March 2014 , pp. 297 - 313
Copyright
Copyright © Royal Aeronautical Society 2014 

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