Project Title:

CFD Methods for Fast Flow Transients Encountered in Non-Linear Combustion Instability

11.04-6576A
CFD Methods for Fast Flow Transients Encountered in Non-Linear Combustion Instability
Problems
CFD Research Corporation
3325-D Triangle Boulevard
Huntsville
AL
35805
Andrzej J.
Przekwas
(205-5536-6576)
MSFC

Abstract:

Rocket thrust chambers often experience combustion instabilities which may result
in reduced performance, increased structural loads, and, ultimately, catastrophic
failure. Existing analytical methods are generally limited to linear-combustion instabilities.
Relatively little has been achieved to understand nonlinear combustion instabilities
primarily because of lack of an urate computational fluid dynamics (CFD) methodology.
This project will concentrate on developing fast, time- and space-accurate CFD methods
for exact analysis of the nonlinear combustion instabilities. The proposed innovative
time-accurate method will be compared with best existing numerical models. The technique
will be evaluated on one-dimensional acoustic and combustion instability problems.
Results will be compared with analytical solutions and available experimental data.
In Phase II, the best technique will be incorporated in a CFD computer code to be
used as a base for incorporating physical models of two-phase spray combustion models.

Potential Commercial Application:

Potential Commercial Applications:  Accurate prediction of nonlinear combustion instabilities
could be used by all rocket manufacturers.