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Evolution of Swirl Boundary Layer and Wall Stall at Part Load - A Generic Experiment

Stapp, Dennis ; Pelz, Peter F. (2022):
Evolution of Swirl Boundary Layer and Wall Stall at Part Load - A Generic Experiment. (Postprint)
2A, In: Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition GT2014 June 16-20, 2014, Düsseldorf, Germany : Turbomachinery,
Darmstadt, ASME, ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, Düsseldorf, Germany, 16.-20.06.2014, ISBN 978-0-7918-4560-8,
DOI: 10.26083/tuprints-00020944,
[Conference or Workshop Item]

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Item Type: Conference or Workshop Item
Origin: Secondary publication service
Status: Postprint
Title: Evolution of Swirl Boundary Layer and Wall Stall at Part Load - A Generic Experiment
Language: English
Abstract:

The influence of Reynolds number, roughness and turbulence on the onset of wall stall is up to now not sufficiently understood. To shed some light onto the interdependency of near wall flow with growing swirl component, the simplest “machine” is tested. The apparatus we examine is a circular pipe at rest followed by a rotating co-axial pipe segment. In the sense of a generic experiment this machine represents a very basic model of the inlet of an axial machine. Due to the wall shear stress a swirl boundary layer is formed in the rotating pipe segment, interacting with the axial boundary layer. The evolution of the swirl velocity profile with increasing axial distance from the rotating pipe inlet is measured for various Reynolds numbers, flow numbers and degrees of turbulence by means of Laser Doppler Anemometry. We observe a self-similarity in the swirl velocity profile, for subcritical flow number and develop a scaling law for the velocity distribution in the transition section of a rotating pipe. At critical flow number the boundary layer is separating, resulting in a ring vortex at the inlet of the rotating pipe. Our work fills the gap of previous experimental works, with respect to high Reynolds numbers and low flow numbers. The parameter field we examine is most relevant for turbomachinery application and wall stall. In addition our boundary layer resolution is sufficient to resolve the swirl boundary layer thickness. Only this high resolution enables us to generalize the experimental findings by means of a similarity distribution of the velocity profile within the swirl boundary layer.

Book Title: Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition GT2014 June 16-20, 2014, Düsseldorf, Germany : Turbomachinery
Series Volume: 2A
Place of Publication: Darmstadt
Publisher: ASME
Collation: 8 Seiten
Classification DDC: 600 Technik, Medizin, angewandte Wissenschaften > 620 Ingenieurwissenschaften
Divisions: 16 Department of Mechanical Engineering > Institute for Fluid Systems (FST)
Event Title: ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
Event Location: Düsseldorf, Germany
Event Dates: 16.-20.06.2014
Date Deposited: 02 May 2022 13:27
Last Modified: 02 May 2022 13:27
DOI: 10.26083/tuprints-00020944
Corresponding Links:
URN: urn:nbn:de:tuda-tuprints-209445
URI: https://tuprints.ulb.tu-darmstadt.de/id/eprint/20944
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