Studies on Transonic Turbine with Film-Cooled Blades
Annual rept. no. 4, 1 Jul 1976-30 Jun 1977
MASSACHUSETTS INST OF TECH CAMBRIDGE GAS TURBINE LAB
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During the fourth year of the contract, further advances were made towards the goal of gathering the heat transfer and aerodynamics flow data necessary for a good understanding of the performance of film-cooled, highly- loaded, transonic turbine blading. Surface Mach number and heat transfer rate distributions were determined for a reference transonic airfoil over a range of exit Mach numbers, for inlet incidence angle variation of or - 15 deg. An evaluation and comparison of all cascade data collected so far was then conducted. Progress was also made in the investigation of the effects of unsteadiness on transonic airfoil aerodynamics and heat transfer.
- Hydraulic and Pneumatic Equipment