G. Rahier, Y. Delrieux

The theoretical methods used a.t ONERA for the blade-vortex interaction noise prediction are described. Predictions are performed in five main steps : rotor trim, wake geometry, interacting vortices, blade pressure and radiated noise. Three ways of introducing the wake influence in unsteady load computations are investigated. The first one supposes that the tip filaments of the wake lattices are dominant. The second one treats all the filaments of the lattices as interacting vortices. The last one aims at modelling the local wake rolling-up and the vortex concentration. For each method, theoretical vortex geometries and intensities, loads, contour plots and acoustic signatures are presented and compared to experiment. They show the benefit of using a roll-up model in BVI computations. Indeed, the tip filament assumption appears not general enough for realistic applications and the whole lattice approach does not seem reliable. On the contrary, fairly good aeroacoustic results are achieved using the roll-up model. Particularly, this modelling allows us to deal with rotor geometries and kinematics which are likely to generate inboard vortices.

First Joint CEAS/AIAA Aeroacoustics Conference, München, 1995

Conference Paper

englisch

21,0 x 29,7 cm, 9 Seiten

DGLR-Bericht, 1995, 1995-01, First Joint CEAS/AIAA Aeroacoustics Conference - Proceedings; S.393-401; 1995; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroacoustics, blade-vortex interaction

Bibliothek

1995