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| Content Provider | The American Society of Mechanical Engineers (ASME) Digital Collection |
|---|---|
| Author | Giel, P. W. Thurman, D. R. Fossen, G. J. Van Hippensteele, S. A. Boyle, R. J. |
| Copyright Year | 1996 |
| Abstract | Turbine blade endwall heat transfer measurements are given for a range of Reynolds and Mach numbers. Data were obtained for Reynolds numbers based on inlet conditions of 0.5 and 1.0 × 106, for isentropic exit Mach numbers of 1.0 and 1.3, and for freestream turbulence intensities of 0.25% and 7.0%. Tests were conducted in a linear cascade at the NASA Lewis Transonic Turbine Blade Cascade Facility. The test article was a turbine rotor with 136° of turning and an axial chord of 12.7 cm. The large scale allowed for very detailed measurements of both flow field and surface phenomena. The intent of the work is to provide benchmark quality data for CFD code and model verification. The flow field in the cascade is highly three-dimensional as a result of thick boundary layers at the test section inlet. Endwall heat transfer data were obtained using a steady-state liquid crystal technique. |
| Sponsorship | International Gas Turbine Institute |
| File Format | |
| ISBN | 9780791878750 |
| DOI | 10.1115/96-GT-180 |
| Volume Number | Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration |
| Conference Proceedings | ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition |
| Language | English |
| Publisher Date | 1996-06-10 |
| Publisher Place | Birmingham, UK |
| Access Restriction | Open |
| Subject Keyword | Turbulence Turbine blades Computational fluid dynamics Cascades (fluid dynamics) Nasa Reynolds number Rotors Flow (dynamics) Liquid crystals Steady state Chords (trusses) Heat transfer Turbines Boundary layers Mach number |
| Content Type | Text |
| Resource Type | Article |
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