Unstructured Density-Based CFD Methodology for Gas Turbine Combustor Applications

Innovative unstructured, density-based CFD methodology will be developed in this project applicable to low-speed, turbulent reacting flows. In Phase I, the feasibility of using finite rate kinetics in an unstructured CFD environment will be addressed. An existing unstructured, density-based, implicit CFD code, CFD FASTRAN, will be used as a starting point. First, the code will be modified for low-speed flows by incorporating existing pre- conditioning matrix methods. Second, at least two multi-step finite-rate hydrocarbon-air combustion models will be implemented and tested. Comparison of computational efficiency will be made to current structured, pressure-based CFD methodology. And last, for full 3-D demonstration, an annular gas turbine combustor will be modeled and analyzed. In Phase II, spray models, conjugate heat transfer, and other advanced physical models required for combustor analysis will be incorporated and validated. The developed unstructured methodology will also be implemented into the NASA LeRC ALLSPD code.