V.V. Golubev, H.M. Atassi

The aerodynamic and acoustic response of a ducted blade row in unsteady swirling flow with imposed upstream vortical disturbance is analyzed. For the present analysis, the swirling mean flow is represented by a superposition of a uniform and a free vortex flows. The unsteady velocity is split into a vortical part and a potential part, with the unsteady pressure depending solely on the latter. It is shown that the vortical velocity has a continuum spectrum of eigenfunctions, while the potential part has both continuum and discrete spectra. If no blades are present, the vorticity disturbance will grow linearly as it propagates downstream, however, ist induced unsteady pressure will decay slowly. The interaction of the vortical disturbance with a blade row gives rise to additional acoustic and evanescent waves. The blades aerodynamic response exhibits significant variation along the blade span when compared to a similar response for a non-swirling mean flow.

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.167-175; 1995; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroacoustics

Bibliothek

1995