Experimental research on rotating detonation with liquid hypergolic propellants |
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Authors: | Shuaijie XUE Hongjun LIU Lixin ZHOU Weidong YANG Hongbo HU Yu YAN |
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Affiliation: | Science and Technology on Liquid Rocket Engine Laboratory, Xi’an Aerospace Propulsion Institute, 710100 Xi’an, China |
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Abstract: | This paper describes experimental research into the initiation and propagation of rotating detonation for liquid Nitrogen TetrOxide (NTO) and liquid MonoMethylHydrazine (MMH). An annular rocket-type combustor without nozzle was designed to investigate detonation combustion. The propellants were injected through unlike impingement injectors. The combustion flame fronts and pressure waves were detected using optical diagnostics and dynamic pressure sensors, respectively. The propagation of rotating detonation was established spontaneously by increasing the mass flow rate of propellants. The velocity of propagation of the flame fronts and pressure waves was nearly equal and reaches supersonic speed. Two different detonation combustion patterns are present, single wave mode and double waves mode. And in double waves mode, the two detonation waves are always counter-rotating. The possibility of rotating detonation initiation in a combustor with nozzle was also checked. Stable rotating detonation can be initialized and sustained at similar operating conditions. |
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Keywords: | Hypergolic Initiation Liquid propellant Nozzle Rotating detonation |
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