Project Title:

A Computer Model for Liquid Jet Atomization in Rocket Thrust Chambers

11.04-6576
A Computer Model for Liquid Jet Atomization
	in Rocket Thrust Chambers
CFD Research Corporation
3313 Bob Wallace Avenue #205
Huntsville, AL 35805
Andrzej J. Przekwas  (205-536-6576)
MSFC -- NAS8-37620

Abstract:

	 Liquid propellant atomization plays a dominant role in stable and efficient operation
of rocket thrust chambers. Despite the recent progress in computational fluid dynamics
(CFD) and spray combustion modelling techniques, no satisfactory approach has yet
been developed for propellant atomization modelling. The major innovative element
of this project is the prediction of the droplet breakup rate and average droplet
diameter after primary atomization. The approach is to predict the wave formation
on the jet surface and its transport. These models will be coupled with the jet embedding
technique of predicting the atomization process. These improvements will be incorporated
into NASA's multi-dimensional, reactive flow code, REFLAN, and tested on the thrust
chamber geometry of the space shuttle main engine.
	Phase I established the feasibility of predicting primary atomization of liquid
propellent coaxial injectors. The developed model used linear stability analysis
of surface-wave dynamics in conjunction with the jet-embedding technique for liquid
jets. Predictions of location, size and frequency of drop formation showed good agreement
with available data for both low-velocity (Rayleigh regime) and high-velocity (atomization
regime) jets.

Potential Commercial Application:

Potential Commercial Application: The physical models and the computer code would
be of significant value to all organizations concerned with the design and operation
of liquid rocket engines as well as other industrial equipment using liquid injectors.