Optimal Turbine Blade Topology for Small Engines

ABSTRACT: The proposed SBIR Phase I research program will investigate the optimization of turbine blades for small engines. The objective is to use a slot-type hole geometry for film cooling. This has long been recognized as the optimal configuration for cooling effectiveness. The research tasks will involve a multidisciplinary approach to optimizing the turbine blade to include the slot cooling holes while maintaining the required maximum material stresses. The research team includes a close collaboration with the University of Notre Dame and Honeywell. This team has the required design experience and working knowledge of engine conditions to ensure a high probability of success. BENEFIT: Improved component and system efficiencies as well as hot section durability continues to be of interest for all advanced gas turbine engines. The proposed Phase I effort will focus on creating a viable design that meets all of the constraints imposed by manufacturing, assembly, and reliability in a modern, small-scale, gas-turbine engine. The successful outcome of Phase I will lead to a Phase II plan in which prototype turbine blades are created and tested in both cascade tunnels and rotating rigs. The intent of the Phase II effort will be to bring a final, optimized design to TRL 6. The commercial products foreseen from this research are multidisciplinary design optimization tools and advanced manufacturing technologies.