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Numerical Investigation of Combustion of Cryogenic H2-O2 Propellant under Sub-Critical Condition

Ghasempour, Arash | 2016

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 48479 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Mardani, Amir; Farshchi, Mohammad
  7. Abstract:
  8. The present work is concerned with numerical simulation of spray flame for rocket combustor (MASCOTTE A-10 test case at 10 bar pressure) based on cryogen gaseous hydrogen and liquid oxygen at specific condition. This liquid oxygen and gaseous hydrogen single element combustor experiment has been the focus of many numerical studies which is representative of combustion in rocket combustion chamber condition. The purposed strategy relies on hybrid Eulerian-Lagrangian framework that continuous phase is evaluated by Reynolds average Navier-stokes (RANS) equation with quick discretization method and dispersed phase of combustion chamber atmosphere is evaluated by discrete phase method (DPM). To evaluate the turbulent parameter of computational domain, K-e model has performed. Also to describe the complex interaction that takes place between turbulent and chemistry, Eddy dissipation concept (EDC) has accomplished. The capabilities of the computation model are evaluated through a detailed comparison with the experimental databases gathered on the ONERA MASCOTTE test bench. Based on these comparisons, it appears that the present investigation has a good approximation of liquid rocket injector flows for subcritical spray combustion
  9. Keywords:
  10. Combustion Simulation ; Eulerian-Lagrangian Approach ; Dispersed Phase ; Cryogenic Propellant ; Numerical Investigation ; Subcritical Condition

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