F. Kameier, T. Nawrot, W. Neise

An experimental investigation is described to identify the aeroacoustic generation mechanism of the tip clearance noise of axial turbomachines. The tip clearance flow is a secondary flow through the radial gap between the blade tip and the casing wall which is driven by the pressure difference between suction side and pressure side of each blade. Tip clearance noise can be a significant source of noise when the tip clearance exceeds a certain limit. It is well known that a small tip clearance is beneficial for both the aerodynamic performance and the noise characteristics of axial flow machines. In this paper experimental results of an ongoing study into the nature of the tip clearance noise are presented. Also, some experimental obversations regarding a hysteresis-type behavior of the aerodynamic fan performance and rotating stall inception are reported.

DGLR/AIAA 14th Aeroacoustics Conference, 1992

Conference Paper

englisch

21,0 x 29,7 cm, 10 Seiten

DGLR-Bericht, 1992, 1992-03, DGLR/AIAA 14th Aeroacoustics Conference - Proceedings; S.250-259; 1992; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroacoustics

Bibliothek

1992