CCS and Power Systems
Advanced Energy Systems - Hydrogen Turbines
Environmental Considerations and Cooling Strategies for Vane Leading Edges in a Syngas Environment
Performer: University of North Dakota
Project No: FE0004588
This collaborative effort studying technologies important to the reliability of high hydrogen fueled gas turbines has been structured utilizing three phases.
Phase I: Leading Edge Model Development and Experimental Validation
The initial task for The Ohio State University's (OSU's) turbine reacting flow rig (TuRFR) facility will be to determine if the deposition mechanism for faired cylinders is similar to deposition for turbine vanes. If this approach is feasible, then the relative impact of leading edge diameter on deposition can be investigated using varying diameter cylinders instead of vanes. The deposition measurements will then be made and sent to the University of North Dakota (UND) for surface modeling. During Phase I, UND will study the response of turbulence approaching large cylindrical stagnation regions, the associated heat transfer augmentation, and boundary layer development on the cylinder's surface. Additionally, UND will begin the development of candidate internal cooling geometries for cooling a region of a turbine vane’s leading edge.
Phase II: Experimental Deposition and Roughness Study
OSU will utilize the TuRFR facility, modified to generate higher levels of turbulence, to study the influence of turbulence on deposition rates in turbines. These results will be used to improve predictive modeling and made available to UND for heat transfer measurements. UND will use surfaces generated by OSU as part of their leading edge heat transfer and boundary layer studies. UND will also develop and test candidate internal cooling schemes for large regions on a turbine vane's leading edge.
Phase III: Mitigation of Deposition Using Downstream Full Coverage Film Cooling
OSU will use faired (rounded to reduce drag) cylinders to explore various film cooling designs to assess their effectiveness at reducing deposition. Actual turbine vane geometry will be used to explore the influence of select film cooling patterns on deposition. UND will investigate the combined influence of turbulence and realistic roughness on film cooling effectiveness and surface heat transfer. As a basis of comparison, they will initially look at the influence of turbulence on film cooling effective-ness and heat transfer for selected full coverage geometries.
Deposit measurements on nozzle guide vane for slot film cooling (left); no film cooling (right).