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- W3185935851 abstract "Although many different annulus geometries have been tested in different rotating detonation rocket engine systems worldwide, parametric studies on various annular gap widths are rare. In the presented study, a geometry that has been characterized over 2000 successful hot-fire tests is modified to perform such a study. Here, the nominal 5~mm gap annulus is compared to a 2.5~mm annulus and a 7.5~mm annulus, representing a 50% decrease in annulus area, and a 50% increase in annulus area, respectively. These three configurations are then compared across a range of equivalence ratios, spanning $bm{0.25leqphileq2.5}$ for constant total mass flow rate, and constant total mass flux. In the case of constant total propellant mass flow rate, it is shown that the smallest annulus has higher chamber pressure, wave speed, and global performance (i.e. thrust and specific impulse). For equivalent total mass flux, the smallest annulus slightly underperforms the other two geometries. This could be due to one or the combination of many factors, which are discussed. One possible contributor--asymmetric injector response as a result of periodic unchoking of the injectors--is shown to be present through examination of the plenum pressures. These results highlight considerations that must be made when scaling the annulus width in future engine design iterations." @default.
- W3185935851 created "2021-08-02" @default.
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- W3185935851 date "2021-07-28" @default.
- W3185935851 modified "2023-09-27" @default.
- W3185935851 title "Rotating Detonation Rocket Engine Scaling using Variable Annular Width Geometries" @default.
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- W3185935851 doi "https://doi.org/10.2514/6.2021-3686" @default.
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