Project Title:

Unstructured Density-Based CFD Methodology for Gas Turbine Combustors

CFD Research Corp.
3325 Triana Blvd.
Huntsville, AL 35805

93-101.01   6576  __      AMOUNT REQUESTED $70,000

Unstructured Density-Based CFD Methodology for Gas Turbine Combustors

Abstract:

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.

The CFD methodology will be packaged into a commercial software
code (as part of Phase III) and licensed to gas turbine engine
manufacturers such as Solar, Westinghouse, Allison, Allied Signal,
General Electric, P&W, etc. The code will have direct application
to combustor design, especially to the NASA High Speed Civil
Transport and Advanced Subsonics Engines. In addition, due to its
ability to model low and high speed flows with finite-rate
chemistry, the code will also be applicable to other engine
components, e.g., inlets, nozzles, etc.

unstructured, finite-rate chemistry, Navier-Stokes, implicit fully
coupled, gas turbine combustors