Investigation of Geometric and Thermal Scaling Effects a Simulated Turbine Vane Leading Edge Model
Abstract
This thesis explores multiple topics, including the relative importance of non-dimensional parameters that relate film cooling performance within different temperature regimes and the effects of different internal cooling configurations on overall film cooling effectiveness. Additionally, the effect on results from geometrically scaled experimental setups was also investigated. Numerous changes were to the FCR were implemented to improve testing performance and to enable the geometric scaling comparisons. An Inconel 718 leading edge model was used to gather thermal measurement data. Four main freestream conditions were used that varied freestream temperature and Reynolds number. Air coolant temperature and mass flow were adjusted to match different film cooling non-dimensional parameters. Comparing the results found that effectiveness scaled well between different temperature regimes when the non-dimensional parameters matched, increased freestream Reynolds number led to decreased effectiveness, and impingement cooling improved the overall effectiveness distribution.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 23, 2018
- Accession Number
- AD1056634
Entities
People
- James G. Tewaheftewa
Organizations
- Air Force Institute of Technology