Abstract
A computational study was carried out to model the high-pressure combustion mechanism in scram accelerator. Fluid dynamic modeling was based on RANS equations for reactive flows and it was solved in a fully coupled manner using fully implicit-upwind TVD scheme. For the accurate simulation of high-pressure combustion in ram accelerator, 9-species, 25-step fully detailed reaction mechanism was incorporated with the existing CFD code previously used in the ram accelerator studies. The mechanism is based on GRI-Mech. 2.11 which includes pressure-dependent rate formulation indispensable for the correct prediction of induction time in high-pressure environment. A real gas equation of state was also included to account for molecular interactions and real gas effects of high-pressure gases. The present combustion modeling is compared with previous ones using 8-step or 19-step mechanisms and ideal gas assumption. The result shows that mixture ignition characteristics are very sensitive to the combustion mechanisms, and the different mechanisms result in completely different reactive flow-field characteristics that have a significant relevance to the operation mode and the performance of scram accelerator.
| Original language | English (US) |
|---|---|
| State | Published - 1999 |
| Externally published | Yes |
| Event | 35th Joint Propulsion Conference and Exhibit, 1999 - Los Angeles, United States Duration: Jun 20 1999 → Jun 24 1999 |
Other
| Other | 35th Joint Propulsion Conference and Exhibit, 1999 |
|---|---|
| Country/Territory | United States |
| City | Los Angeles |
| Period | 06/20/99 → 06/24/99 |
Bibliographical note
Publisher Copyright:© 1999 by B.-J. Lee, J.-Y. Choi, I.-S. Jeung and Y. Yoon. Published by the American Institute of Aeronautics and Astronautics, Inc.
ASJC Scopus subject areas
- Energy Engineering and Power Technology
- Electrical and Electronic Engineering
- Mechanical Engineering
- Control and Systems Engineering
- Aerospace Engineering