Transient heat transfer properties in a pulse detonation combustor

Abstract

The heat transfer along the axis of a pulse detonation combustor has been characterized for various frequencies and fill fractions at 2.5 atmospheres of pressure for chamber refresh conditions. In a pulse detonation combustor, a supersonic detonation wave is the method for transforming chemical energy into mechanical energy and the wave propagates much faster than the subsonic flames in devices such as rockets and ramjets. The flow field inside a pulse detonation combustor is highly turbulent, unsteady, and varies largely during each combustion cycle. By determining the heat transfer properties at multiple axial locations and the associated combustor wall temperatures, proper combustor material selection can ensure the material properties will not deteriorate and therefore allow for practical operational lifetimes. Experimental testing measured the axial heat transfer characteristics in a pulse detonation combustor at various operating conditions and multiple cooling jacket locations. Computer simulations were used to model the heat transfer inside the pulse detonation combustor and correlate those predications with empirical data. The acquired data from the comparison of the computer simulations and the experimental results was correlated and demonstrated good agreement. The determined values should allow designers the ability to consider regenerative fueling strategies for future systems.