| Περίληψη: | This thesis concerns the simulation of the isothermal mixing field as well as the reacting
of a Tay-type gas turbine combustor (Rolls Royce Tay). First, a brief description of combustion
is given, various important combustion parameters are mentioned and combustion problems are
classified accordingly. Then, the main types of combustors are presented, mainly used in
aeronautical applications for aircraft propulsion, and the main design requirements are
highlighted. Then the basic equations that govern combustion problems are presented, such as
the conservation of momentum, mass, species mass etc, and are appropriately modeled to be
applied to our problem. For the present study, the Partially Stirred Reactor (PaSR) model was
used and the turbulence was modeled with the Lilly-Smagorisnky LES model. The fuel used was
the propane and for the chemical reactions modeling , two-step reduced reaction mechanism was
used. The boundary conditions used for the simulation are explained, as well as the
simplifications and assumptions made. The geometry and the mesh were generated in the opensource software Salome and the simulation was executed in the also open-source OpenFOAM.
The results were compared with the experimental measurements of Heitor and Whitelaw [2], and
closing the thesis, conclusions are presented and future studies are suggested.
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