C. Clemen, V. Gümmer

A new method for the three-dimensional design of blades for axial-flow compressors has been developed. This new method incorporates the systematic application of sweep and dihedral at hub and tip and introduces three-dimensional inversely calculated camber-lines for a prescribed three-dimensional load distribution into the blade design. The resulting blade shape matches the three-dimensional flow environment and achieves a large reduction in secondary losses. This can be achieved by significantly improving the rotor tip clearance flow and the rotor hub comer separations. With this improvement of the behavior of the secoridary flow phenomena a considerable increase in rotor and stage efficiency as weil as stability was obtained compared to modern conventionally designed blades. The new method has been applied to the design of a rotor for a highly-loaded single-stage axial-flow low-speed research compressor and was validated by means of 3D-Navier-Stokes calculations and experiments giving an increase in design point stage efficiency of 1.5% and a 20% improvement in stall range.

Deutscher Luft- und Raumfahrtkongress 2010

Conference Paper

englisch

21,0 x 29,7 cm, 12 Seiten

Deutscher Luft- und Raumfahrtkongress Tagungsband - Manuskripte, 2010, 2010, ; S.1203-1214; 2010; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

compressor rotor

Bestellbar

2010