A New Test Facility to Investigate Film Cooling on a Nonaxisymmetric Contoured Turbine Endwall—Part II: Heat Transfer and Film Cooling Measurements
| Autor: | Hans-Jörg Bauer, Johannes Kneer, Achmed Schulz, Franz Puetz |
|---|---|
| Rok vydání: | 2016 |
| Předmět: |
020301 aerospace & aeronautics
Materials science Mechanical Engineering Reynolds number Mechanical engineering 02 engineering and technology Mechanics Aerodynamics 01 natural sciences Turbine 010305 fluids & plasmas Coolant symbols.namesake 0203 mechanical engineering Heat flux Mach number Cascade 0103 physical sciences Heat transfer symbols |
| Zdroj: | Journal of Turbomachinery. 138 |
| ISSN: | 1528-8900 0889-504X |
| DOI: | 10.1115/1.4032364 |
| Popis: | The present work is part of a comprehensive heat transfer and film-cooling study on a locally cooled non-axisymmetric contoured turbine endwall. A new test rig consisting of a linear cascade of three prismatic vanes at unity scale and exchangeable endwall has been established. The rig is operated in an open-loop configuration at a reduced main gas temperature of 425 K, an exit Mach number of 0.5 and an exit Reynolds number of 1.6×106. Air is used both as main gas and coolant; a realistic density ratio is achieved by cooling the coolant below freezing. In Part I [1] of the study aerodynamic measurements are presented. This paper concentrates on film-cooling of the contoured endwall with special emphasis on data acquisition and reduction for the application of the superposition principle of film cooling. The first experimental results from thermographic measurements are discussed.Copyright © 2015 by ASME |
| Databáze: | OpenAIRE |
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