Combustion response of a premixed swirl injector to longitudinal acoustic oscillations

T. Wang, V. Yang

研究成果: Paper同行評審

4 引文 斯高帕斯(Scopus)

摘要

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.

原文English
出版狀態Published - 1997
事件35th Aerospace Sciences Meeting and Exhibit, 1997 - Reno, United States
持續時間: 1997 一月 61997 一月 9

Other

Other35th Aerospace Sciences Meeting and Exhibit, 1997
國家United States
城市Reno
期間97-01-0697-01-09

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

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