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ISSN Online: 2377-424X

ISBN Print: 978-1-56700-474-8

ISBN Online: 978-1-56700-473-1

International Heat Transfer Conference 16
August, 10-15, 2018, Beijing, China

EXPERIMENTAL RESEARCH OF SUPERSONIC AERODYNAMIC COOLING EFFECT AND ITS APPLICATION FOR HIGHER ENERGY SEPARATION EFFICIENCY

Get access (open in a dialog) DOI: 10.1615/IHTC16.cov.021244
pages 2987-2994

摘要

Supersonic aerodynamic cooling effect implies adiabatic wall temperature decreasing in the wake of different obstacles like ribs, wedges or steps. This effect together with heat transfer enhancement in separated and reattached boundary layer can be utilized for higher efficiency of a new method of gas dynamic energy separation. This method is based on thermal interaction of subsonic and supersonic flows through a heat conducting partition resulting in heating of a supersonic flow and cooling of subsonic one. Experimental results are given for separated supersonic flow influence on adiabatic wall temperature of plane model. Rib height was varied from 2 to 10 mm. Thickness of the boundary layer at the nozzle exit section was about 6 mm. Initial flow Mach number was 2.25. Reynolds number based on the distance from the nozzle throat was about 2.5·107. Total temperature was 293K. Experiments were conducted with the use of National Instruments equipment, LabView powered automation programs, optical visualization, thermocouples with thermal compensation. Graphs of the change during experiment are presented for total, wall and adiabatic wall temperature. In result of the study field distribution of adiabatic wall temperature, temperature recovery factor and Stanton number enhancement were presented along the experimental model for a separated wake flow behind the rib in comparison with a smooth model flow without any disturbances. The results demonstrate potential applicability of supersonic aerodynamic cooling effect for higher efficiency of gas dynamic energy separation process.