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CFD modeling of kerosene combustion with various initial conditions and fuel droplet diameters
(НТУ "ХПИ", 2015) Hajivand, Masoud
This paper presents the numerical models for the analysis of combustor fuel spray, characteristics, in various injection conditions in a can type of combustor with a double stage radial swirler. Spray consists of two fundamental and consecutive steps, means the primary breakup and the secondary breakup. The primary breakup is modeled by Linearized Instability Sheet Atomization (LISA) which are mostly used in a pressure swirl atomizers. Secondary breakup is modeled by Taylor analogy breakup model (TAB). The trajectory and velocity of generated fuel droplets is determined by Lagrangian Particle Tracking. Characteristics of jet breakup, depends on a variety of factors such as turbulence, injection pressure drop, velocity profiles, nozzle geometry, and the physical state of the liquid fuel. In this paper Jet-A aviation fuel (kerosene), modeled as a two-component surrogate fuel (by mass 60 % C10H22 and 40 % C9H12). The standard k–ε model with the enhanced wall treatment and the Euler-Lagrange method were employed for the simulation of the turbulence and spray. All results of the simulation in this paper are analyzing in 3 various injection conditions and one of these cases was chosen and implemented in a real annular combustion chamber of a gas turbine. A PDF Flamelet model was employed to simulate combustion process.