Abstract
A study was conducted to investigate flame transition in dual-mode scramjet combustor with oxygen piloted ignition. The heat sink combustor model was made of stainless steel and could be divided into four segments. A strut was mounted in the center of the combustor for fuel injection and flame holding. Pressure taps were installed at the centerline of the combustor side wall with the range 0-1 MPa and its error was ±0.25% in full scale and the frequency was 500 Hz. The wall pressure distribution was used to calculate the one-dimensional (1D) Mach number distribution along the combustor based on a proposed analysis approach to obtain an estimate of the axial distribution of flow properties in dual-mode scramjet combustor. The pressure and Mach number distribution analyses showed that different combustion modes had been attained in this dual-mode combustor model.
| Original language | English |
|---|---|
| Pages (from-to) | 1103-1107 |
| Number of pages | 5 |
| Journal | Journal of Propulsion and Power |
| Volume | 30 |
| Issue number | 4 |
| DOIs | |
| State | Published - 2014 |
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