Studies on Transonic Turbine with Film-Cooled Blades
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1977
- Accession Number
- ADA052423
Entities
People
- F. Hajjar
- J. F. Louis
- N. Adams
- R. F. Topping
Organizations
- Massachusetts Institute of Technology