Minimization of the Effects of Secondary Reactions on Turbine Film Cooling in a Fuel Rich Environment
Abstract
The demand for increased thrust, higher engine efficiency, and reduced fuel consumption has increased the turbine inlet temperature and pressure in modern gas turbine engines. The outcome of these higher temperatures and pressures is the potential for unconsumed radical species to enter the turbine. Because modern cooling schemes for turbine blades involve injecting cool, oxygen rich air adjacent to the surface, the potential for reaction with radicals in the mainstream flow and augmented heat transfer to the blade arises. This study evaluated various configurations of multiple cylindrical rows of cooling holes in terms of both heat release and effective downstream cooling. It confirmed that a build-up of rows of coolant could be used to effectively protect the wall in a fuel-rich environment. It demonstrated slot and trench configurations to be effective in reducing the heat flux to the wall. Also, the Swirler and Two Row Upstream configurations were shown to highly increase radical consumption. Finally, this research developed infrared imaging as a technique for evaluating the wall temperature of the film cooled surface.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 02, 2014
- Accession Number
- ADA602973
Entities
People
- Andrew T. Shewhart
Organizations
- Air Force Institute of Technology