Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

Abstract

This study explores the effect of differing inlet and outlet boundary conditions on the operation and performance of a rotating detonation combustor (RDC) over an annulus mass flux range of 50 to 210 kg • s −1 • m −2

An alternative architecture of the Humphrey cycle and the effect of fuel type on its efficiency

“…Each cycle layout has been analyzed for hydrogen and DME as a fuel. Hydrogen is the major fuel used for pressure‐gain combustion applications 4 and is thus considered a reference fuel for the present study. Dimethyl ether (DME) was chosen as a fuel due to its excellent ignitability 37,38 and is prior use for shockless explosion combustion studies.…”

“…The resulting T tout and p tout are inserted in Equations (1)- (4). The values of T int and is PGC are computed from these equations iteratively so that the model delivers p 3 = p tout and T 3 = T tout for the same combustion equivalence ratio.…”

“…1 At the same time, theoretical and experimental studies of detonative combustion concepts came to the conclusion that pressure gain up to 30% might be possible for pulsed detonation combustion 2,3 and rotating detonation combustion. [4][5][6] This great potential has motivated numerous thermodynamic cycle performance studies. Initially, most focused on the generation of thrust from pulse detonation combustors.…”

“…Experimental studies on resonant pulsed combustors have demonstrated a pressure gain of approximately 3% 1 . At the same time, theoretical and experimental studies of detonative combustion concepts came to the conclusion that pressure gain up to 30% might be possible for pulsed detonation combustion 2,3 and rotating detonation combustion 4‐6 …”

Rotating Detonation Wave Direction and the Influence of Nozzle Guide Vane Inclination

“…The experiments in this study were carried out with the 90 mm outer diameter RDC developed at Technische Universität Berlin [38,39]. This combustor uses a radially inward configuration for the combustion air, injecting into the combustion annulus through a slot of 1 or 1.6 mm height, resulting in an injector to annulus area ratio (A 3.1 ∕A 3.2 ) of 0.14 or 0.23.…”