Abstract
The combustion response of a premixed swirl injector to longitudinal acoustic oscillations has been studied. Two approaches have been utilized to construct a systematic analysis for flow motions under steady and unsteady conditions. A three-dimensional steady-state flow calculation is first conducted to form a basis for the analysis of unsteady flow motions. The formulation is based on the complete conservation equations with finite-rate chemical kinetics and is solved numerically using a preconditioning technique. Detailed mean flowfields are investigated in depth. The predicted flame shape shows good agreement with experimental observations. An approximate integral technique which incorporates the steady-state results is then developed to study the injector flame response to acoustic disturbances impinging from upstream and downstream regions. The acoustic transmission and reflection properties of the flame region are obtained over a broad range of frequency and operating conditions.
| Original language | English |
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| Publication status | Published - 1997 |
| Event | 35th Aerospace Sciences Meeting and Exhibit, 1997 - Reno, United States Duration: 1997 Jan 6 → 1997 Jan 9 |
Other
| Other | 35th Aerospace Sciences Meeting and Exhibit, 1997 |
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| Country | United States |
| City | Reno |
| Period | 97-01-06 → 97-01-09 |
All Science Journal Classification (ASJC) codes
- Space and Planetary Science
- Aerospace Engineering