Swirl Injector Modeling for Cryogenic Propulsion

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Yousefi, Alireza | 2014

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 45839 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Morad, Mohammad Reza
Abstract:
Flow analysis in and out of the pressure-swirl injector in supercritical condition is investigated in this thesis. These injectors widely are used in different industries such gas turbine combustion chamber and liquid fuel rockets. Flow simulation in these injectors is so complex because of existence of gas core in axial region and high swirl and axial speeds in injectors. Unlike subcritical condition, droplet and ligament don’t form in supercritical condition so injector performance represents with two parameters including liquid film thickness in vortex chamber and liquid spreading angle. Mass flow, geometric constant, length and the distance between tangential inlet and injector head, are the main parameters that effect on liquid thickness and spreading angle. In this thesis mass flow and geometric constant effeteness on liquid thickness will be observed. Single phase flow condition is considered in this simulation. Cubic state and NIST real gas equation also are used for supercritical condition simulation. Turbulent flow simulation is performed with RNG K-ε turbulent model. Also another simulation is performed using laminar flow solution
Keywords:
Swirl Injector ; State Equation ; Turbulent Model ; Axisymmetric Model ; Supercritical Condition

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