Turbulent Detonation Transition In A Linearized Rotating Detonation Engine

Abstract

An experimental investigation to characterize flame and detonation propagation dynamics within a Rotating Detonation Engine (RDE) using a hydrogen air mixture is conducted. Using a transition that directs flow from an RDE to a linear channel, the fast propagating flame of interest can be easily observed and probed. The linear facility is designed to mimic the flow conditions of the RDE, issuing reactants axially into the channel to drive continued flame development. An exact prediction of the flame, DDT and detonation behavior in an RDE is very difficult and requires thorough exploration, through which a linear configuration can provide access. Schlieren imaging techniques and dynamic pressure transducers are utilized to capture wave propagation velocities, peak pressures and the flow field structures. An important factor in the classification of flame dynamics and DDT onset in the RDE is the turbulence level that generates favorable conditions for the spontaneous ignition of a detonation. Turbulent fluctuations are varied using different geometrical configurations. The goal is to set similar RDE conditions and observe the resulting wave mechanics of fast deflagrated flames and detonation initiation within the RDE. The experimental work in the linear channel aims to to improve the ability to predict and control the time and location of detonation onset within the RDE geometry.

Publication Date

1-1-2018

Publication Title

AIAA Aerospace Sciences Meeting, 2018

Issue

210059

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

DOI Link

https://doi.org/10.2514/6.2018-1416

Socpus ID

85044583324 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/85044583324

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