Consideration of structural constraints in passive rotor blade design for improved performance

Author:

Lim J.W.

Abstract

ABSTRACTThis design study applied parameterisation to rotor blade for improved performance. In the design, parametric equations were used to represent blade planform changes over the existing rotor blade model. Design variables included blade twist, sweep, dihedral and the radial control point. Updates to the blade structural properties with changes in the design variables allowed accurate evaluation of performance objectives and realistic structural constraints – blade stability, steady moments (flap bending, chord bending and torsion) and the high-g manoeuvre pitch link loads. Performance improvement was demonstrated with multiple parametric designs. Using a parametric design with advanced aerofoils, the predicted power reduction was 1.0% in hover, 10.0% at μ = 0.30 and 17.0% at μ = 0.40, relative to the baseline UH-60A rotor, but these were obtained with a 35% increase in the steady chord bending moment at μ = 0.30 and a 20% increase in the half peak-to-peak pitch link load during the UH-60A UTTAS manoeuvre. Low vibration was maintained for this design. More rigorous design efforts, such as chord tapering and/or structural redesign of the blade cross section, would enlarge the feasible design space and likely provide significant performance improvement.

Publisher

Cambridge University Press (CUP)

Subject

Aerospace Engineering

Reference27 articles.

1. Yeo H. , Bousman W.G. and Johnson W . Performance analysis of a utility helicopter with standard and advanced rotors, American Helicopter Society Aerodynamics, Acoustics, and Test an Evaluation Technical Specialists Meeting Proceedings, January 2002, San Francisco, California, US.

2. Norman T.R. , Shinoda P. , Peterson R.L. and Datta A . Full-scale wind tunnel test of the UH-60A airloads rotor, American Helicopter Society 67th Annual Forum Proceedings, 3-5 May 2011, Virginia Beach, Virginia, US.

3. Hodges D.H. and Dowell E.H. Nonlinear equations of motion for the elastic bending and torsion of twisted nonuniform rotor blades, NASA TN D-7818, December 1974.

4. Johnson C.S. and Barakos G.N. Optimising aspects of rotor blades in forward flight, Proceedings of the 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 4-7 January 2011, Orlando, Florida, US.

5. Min B.Y. , Sankar L.N. , Collins K. and Brentner K.S. CFD-CSD coupled study in the BVI characteristics of a saw-tooth blade planform, American Helicopter Society 67th Annual Forum Proceedings, 3-5 May 2011, Virginia Beach, Virginia, US.

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