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Liquid propellant rocket engine combustion simulation with a time-accurate CFD method
- Source :
- Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion.
- Publication Year :
- 1993
- Publisher :
- United States: NASA Center for Aerospace Information (CASI), 1993.
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Abstract
- Time-accurate computational fluid dynamics (CFD) algorithms are among the basic requirements as an engineering or research tool for realistic simulations of transient combustion phenomena, such as combustion instability, transient start-up, etc., inside the rocket engine combustion chamber. A time-accurate pressure based method is employed in the FDNS code for combustion model development. This is in connection with other program development activities such as spray combustion model development and efficient finite-rate chemistry solution method implementation. In the present study, a second-order time-accurate time-marching scheme is employed. For better spatial resolutions near discontinuities (e.g., shocks, contact discontinuities), a 3rd-order accurate TVD scheme for modeling the convection terms is implemented in the FDNS code. Necessary modification to the predictor/multi-corrector solution algorithm in order to maintain time-accurate wave propagation is also investigated. Benchmark 1-D and multidimensional test cases, which include the classical shock tube wave propagation problems, resonant pipe test case, unsteady flow development of a blast tube test case, and H2/O2 rocket engine chamber combustion start-up transient simulation, etc., are investigated to validate and demonstrate the accuracy and robustness of the present numerical scheme and solution algorithm.
- Subjects :
- Fluid Mechanics And Heat Transfer
Subjects
Details
- Language :
- English
- Database :
- NASA Technical Reports
- Journal :
- Eleventh Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion
- Publication Type :
- Report
- Accession number :
- edsnas.19950017025
- Document Type :
- Report