Low Pressure Turbine Endwalls
The endwall flow that forms at the root of low pressure turbine blades contains a complex vortex system and three-dimensional boundary layer separation. This is highly relevant to the propulsion community since it represents a source of significant energy losses in gas turbine engines. Improvements in the understanding and prediction of these flow features are required to increase efficiency and reduce engine weight, both of which would have dramatic impacts on the gas turbine community. The TFCL investigates endwall flow physics in collaboration with the Air Force Research Laboratory at Wright Patterson Air Force Base (Dr. Rolf Sondergaard).
Figure: Endwall flow structure for L2F baseline and L2F-EF (Endwall Fillet) showing in-plane velocity vectors superimposed on out-of-plane vorticity contours.
Keigth Sangston, Jesse Little, M. Eric Lyall, and Rolf Sondergaard. "Effect of Blade Profile Contouring on Endwall Flow Structure in a High-Lift-Low-Pressure Turbine Cascade," Journal of Turbomachinery, Vol. 139, No. 2 (2016). https://doi.org/10.1115/1.4034480.