Accession Number : AD1010300


Title :   Fundamental Structure of High-Speed Reacting Flows: Supersonic Combustion and Detonation


Descriptive Note : Technical Report,01 Mar 2013,31 Mar 2016


Corporate Author : University of Maryland College Park United States


Personal Author(s) : Yu,Kenneth H ; Burr,Jason ; Fievisohn,Robert


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/1010300.pdf


Report Date : 30 Apr 2016


Pagination or Media Count : 35


Abstract : An experimental investigation on detonation wave propagating across a row of reactant jets in a narrow channel has been performed. The principal objective of the research was to gain better understanding of the fundamental flow structure in a rotating detonation engine (RDE). A linear channel simulating an unwrapped RDE annulus was used for the investigation with an array of fifteen injectors lining the inlet plane. The resulting flow structure caused by a detonation wave propagating across the array of reactant jets was examined as a function of reactant composition and flow rates. This setup served as the baseline configuration for investigating the RDE flowfield with the curvature effect. T he overall research effort comprised of the following technical elements: (1) blast wave propagation under partial confinement, (2) detonation wave experiments in a transvers flow channel, (3) modeling of detonation wave in transvers flow using a method of characteristics approach. The specific objectives and results of the research of each of these program elements are summarized in this report.


Descriptors :   blast waves , wave propagation , liquid propellant rocket engines , flow fields , experimental design , Supersonic Combustion


Subject Categories : Liquid Propellant Rocket Engines
      Combustion and Ignition
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE