Abstract
A short duration (0.4 sec) test facility, capable of testing 0.5-meter diameter, film-cooled, high work aircraft turbine stages at rigorously simulated engine conditions has been designed, constructed, and tested. The simulation capability of the facility extends up to 40 atm inlet pressure at 2500°K (4000°F) turbine inlet temperatures. The facility is intended primarily for the exploration of unsteady, threedimensional fluid mechanics and heat transfer in modern turbine stages.
Cite
CITATION STYLE
Epstein, A. H., Guenette, G. R., & Norton, R. J. G. (1984). THE MIT BLOWDOWN TURBINE FACILITY. In Proceedings of the ASME Turbo Expo (Vol. 4). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/84-GT-116
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