Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths
نویسندگان
چکیده
A rotating detonation rocket engine (RDRE) with various convergent nozzles and chamber lengths is investigated. Three hundred hot-fire tests are performed using methane oxygen ranging from equivalence ratio equaling 0.5–2.5 total propellant flow up to 0.680 kg/s. For the full-length (76.2 mm) study, three at contraction ratios ϵc = 1.23, 1.62 2.40 tested. Detonation exhibited for each geometry equivalent conditions, only fuel-rich operability slightly increased nozzles. Despite this, counter-propagation, i.e., opposing wave sets, becomes prevalent increasing constriction. This accompanied by higher number of waves, lower speed Uwv unsteadiness. Therefore, most constricted nozzle always has lowest Uwv. In contrast, performance increases constriction, where thrust specific impulse linearly increase a 27% maximum increase. Additionally, two half-length (38.1 chambers studied including straight nozzle; these shortened geometries show equal their longer equivalent. Furthermore, existence counter-propagation minimized. Accompanying high-fidelity simulations injection recovery analyses describe underlying physics driving dynamics, suggesting physical throat/injector interaction influences counter-propagation.
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ژورنال
عنوان ژورنال: Energies
سال: 2021
ISSN: ['1996-1073']
DOI: https://doi.org/10.3390/en14082037