Computational Evaluation of Rotor Alone Noise-Reference-Cited by-同舟云学术

Computational Evaluation of Rotor Alone Noise

Published:2023-07-29 Issue: Volume: Page:340-346
ISSN:0972-950X
Container-title:Journal of Aerospace Sciences and Technologies
language:
Short-container-title:joast

Author:

Venkatesan Rahul

Abstract

Transonic 2-Dimensional flow past the rotor was simulated to predict the pressure variation past the rotor through the CFD software ANSYS-Fluent. The mesh generated was found to have a direct impact on capturing the shock and effect of change in the angle of attack through the flow past the rotating blades were found to vary the strength of the passage shock between the blades. The effect of blade geometry on the fan noise radiated near field and far field were investigated. Through the effect of grid refinement, change of chord length and thickness the noise generated by the rotor was found to reduce considerably to an extent. The effect of blade geometry on the fan noise was also studied. The results were in good agreement with the available data from the literature which was evident from the N-waveform.

Reference5 articles.

1. Dupere, I.D.J., MACE 61131 Aero-acoustics, Lecture Notes-7, University of Manchester, School of MACE, 2014.

2. Envia, E., "Fan Noise Reduction: An Overview", AIAA Journal, 2001. 3. Dupere, I.D.J., Dawes, W.N., Wilson, A.G. and Tester, B.J., "Prediction of Rotor Alone Tones in a Transonic Fan Using Steady CFD", AIAA Journal, 1999.

3. Dupere, I.D.J., Dawes, W.N., Wilson, A.G., and Tester, B.J., "Prediction of Multiple Tone Noise and Distortion Noise in a Transonic Fan Using Unsteady CFD", 4th European Conference of Turbomachinery, Fluid Dynamics and Thermodynamics, Italy, 2001.

4. Schulten, J. B. H. M., "Effects of Asymmetric Inflow on Near-Field Propeller Noise, AIAA Journal, 1995.

5. Brentner, K. S., "An Effecient and Robust Method for Predicting Helicopter Rotor High-Speed Impulsive Noise", AIAA Journal, 1996.