Project Title:

Modeling of Turbulent Spray Combustion in Liquid Rocket Engine Components

11.03-6576
Modeling of Turbulent Spray Combustion in
	Liquid Rocket Engine Components
CFD Research Corporation
3313 Bob Wallace Avenue #205
Huntsville, AL 35805
Ashok K. Singhal  (205-536-6576)
MSFC -- NAS8-37619

Abstract:

	 Recent advances in computational fluid dynamics (CFD) provide a basic mechanism
for detailed analyses of the complex combustion processes in liquid rocket engines.
However, the application of CFD techniques to rocket engines requires adequate models
for the physical processes involved: atomization and spray formation under sub- and
super-critical conditions, droplet-droplet interaction, turbulence, mass transfer
via evaporation and diffusion, and combustion of dilute and dense sprays.
	In Phase I, an interim version of the code (named REFLEQS) was developed by the
systematic modification and validation of an existing CFD code. Modifications included
the implementation of advanced numerical methods and advanced turbulence models.
The validation study included six benchmark problems selected to assess individually
the code's capability in numerical analysis and turbulent processes. Results of the
validation study indicated that: central differencing with artificial damping significantly
reduced numerical diffusion; the modified SIMPLEC solution algorithm greatly enhanced
the code's convergence rate and robustness, e.g. its capability of handling highly
non-uniform (high cell aspect ratio) grids; and the extended k- turbulence model
and the multi-scale turbulence model outperformed the standard k- turbulence model.
In addition, the code's capabilities of simulating reactive flows and of using body-fitted
coordinates were demonstrated separately.

Potential Commercial Application:

Potential Commercial Application: These computer codes would be engineering analysis
tools of interest to all organizations involved in rocket propulsion, aircraft engines,
and other liquid fuel combustors.