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Magnus Compressor

Titel Englisch Magnus Compressor
Gesuchsteller/in Rose Martin George
Nummer 103483
Förderungsinstrument Projektförderung (Abt. I-III)
Forschungseinrichtung Institut für Energietechnik ETH Zürich
Hochschule ETH Zürich - ETHZ
Hauptdisziplin Maschineningenieurwesen
Beginn/Ende 01.10.2004 - 30.09.2006
Bewilligter Betrag 132'452.00
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Keywords (6)

COMPRESSOR; MAGNUS EFFECT; TURBOMACHINERY; STALL; Magnus Rotors; axial flow compressor

Lay Summary (Englisch)

Lay summary
Magnus Compressor

This two year project consisted of an experimental and computational study of a new type of turbomachine. The new machine in question was a “Magnus Compressor”. The generic type of machine under study was an axial flow compressor. Specifically a low speed research axial flow compressor known as “Rheinfall” in LSM at ETH Zürich was used as a test vehicle. Rheinfall was modified, a conventional stator made of aerofoils was replaced by a novel type of stator made of a number of cylinders rotating about their axes. The cylinders are known as Magnus rotors, these have been known to science for more than 100 years. Magnus rotors are capable of generating extremely high lift forces. In the Rheinfall compressor lift coefficients were demonstrated more than ten times the level of the conventional stators they replaced (4.5 cf 0.36). The compressor continued to operate with slightly enhanced stability.

In preparation for possible future work the Magnus compressor was redesigned to further push the performance of the Magnus Stator. The aim was to demonstrate levels of lift and diffusion quite impossible for conventional stators. These designs are detailed in the final report and could be built and tested.

Detailed multi-block CFD calculations using the code “Stage 3D” were carried out for a variety of operating points. The hub leakage of the rotating cylinders with rotating end plates and large fillet radii proved a substantial challenge. However, eventually the flow field was predicted and a reasonable level of agreement found in terms of lift, velocity field and global total pressure distribution. The total loss was somewhat under predicted
Direktlink auf Lay Summary Letzte Aktualisierung: 21.02.2013

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