Ulrich Doll
Department of Engine Measurement Systems Institute of Propulsion Technology, German Aerospace Center (DLR) Linder Hoehe, 51147 Cologne, Germany
Eike Burow
Department of Engine Measurement Systems
Institute of Propulsion Technology, German Aerospace Center (DLR) Linder Hoehe, 51147 Cologne, Germany
Manfred Beversdorff
Department of Engine Measurement Systems
Institute of Propulsion Technology, German Aerospace Center (DLR) Linder Hoehe, 51147 Cologne, Germany
Guido Stockhausen
Department of Engine Measurement Systems
Institute of Propulsion Technology, German Aerospace Center (DLR) Linder Hoehe, 51147 Cologne, Germany
Christian Morsbach
Department of Numerical Methods Institute of Propulsion Technology, German Aerospace Center (DLR) 1Linder Hoehe, 51147 Cologne, Germany
Christian Willert
Department of Engine Measurement Systems
Institute of Propulsion Technology, German Aerospace Center (DLR) Linder Hoehe, 51147 Cologne, Germany
Daniel Schluss
Department of Numerical Methods Institute of Propulsion Technology, German Aerospace Center (DLR) 1Linder Hoehe, 51147 Cologne, Germany
Martin Franke
Department of Numerical Methods Institute of Propulsion Technology, German Aerospace Center (DLR) Mueller-Breslau-Str. 8, 10623 Berlin, Germany
要約
The flow field of a Ranque-Hilsch vortex tube is characterized
experimentally. Firstly conventional probe based technology is used in order to measure inlet and outlet temperatures as well as to acquire temporally resolved wall pressure data over a wide range of operating conditions. Secondly the filtered Rayleigh scattering technique is employed in order to gather detailed temporally averaged planar information on the vortex tube's flow topology. These measurements form the basis of a detailed numerical study in part II of this contribution.