Mixing, chemical reaction and flow field development in ducted rockets
Calculations have been made of the three-dimensional mixing, chemical reaction, and flow field development in a typical ducted rocket configuration. The governing partial differential equations are numerically solved by an iterative finite-difference solution procedure. The physical models include the k approx. epsilon turbulence model, one-step reaction, and mixing controlled chemical reaction rate. Radiation is neglected. The mean flow structure, fuel dispersal patterns, and temperature field are presented in detail for a base configuration with 0.058 m (2 in.) dome height, 45/sup 0/ side arm inclination, and with gaseous ethylene injected from the dome plate at an eccentric location. In addition, the influences of the geometrical parameters such as dome height, inclination of the side arms, and location of the fuel injector are studied.
- Research Organization:
- Argonne National Lab., IL (USA)
- DOE Contract Number:
- W-31-109-ENG-38
- OSTI ID:
- 6447794
- Report Number(s):
- ANL-84-62; ON: DE85002710
- Country of Publication:
- United States
- Language:
- English
Similar Records
Computation of turbulent reacting flow in a solid-propellant ducted rocket
Parametric evaluation of ducted fuel injection in an optically accessible mixing-controlled compression-ignition engine with two- and four-duct assemblies
Related Subjects
ROCKETS
CHEMICAL REACTIONS
COMBUSTION
DIFFERENTIAL EQUATIONS
DUCTS
ETHYLENE
MIXING
RAMJET ENGINES
TEMPERATURE DISTRIBUTION
TURBULENCE
ALKENES
ENGINES
EQUATIONS
HEAT ENGINES
HYDROCARBONS
INTERNAL COMBUSTION ENGINES
ORGANIC COMPOUNDS
OXIDATION
THERMOCHEMICAL PROCESSES
421000* - Engineering- Combustion Systems