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Analytical Models for the Thrust of a Rotating Detonation Engine

Shepherd, J.E. and Kasahara, J. (2017) Analytical Models for the Thrust of a Rotating Detonation Engine. GALCITFM, FM2017.001. , Pasadena CA. (Unpublished) http://resolver.caltech.edu/CaltechGALCITFM:2017.001

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Abstract

Two models are proposed for rotating detonation engine performance. The first model is motivated by models of pulse detonation engine performance which are based on the pressure-time history within the detonation tube. The present work extends those ideas to treat rotating detonation engines with a control volume analysis that considers the forces within the combustion chamber. The key scaling parameters for this model are the height of the reactant layer just ahead of the detonation wave and the computed Chapman-Jouguet pressure and velocity. The thrust can be estimated using these parameters and a simple functional form of the pressure history on the injector surface. The second model is based on the approximation of mean axial flow and uses a conventional control volume analysis that focuses on exit conditions to evaluate thrust. The axial flow speed and thrust are evaluated based on approximating the flow following the detonation as isentropic and considering a two-dimensional expansion that converts azimuthal motion into purely axial flow. Numerical and analytic evaluation of these models demonstrates that predicted thrust and specific impulse exhibit the same scaling relationships with mixture properties as pulse detonation engines.


Item Type:Report or Paper (Technical Report)
ORCID:
AuthorORCID
Shepherd, J.E.0000-0003-3181-9310
Contact Email Address:joseph.e.shepherd@caltech.edu
Additional Information:The authors thank the Japan Society for the Promotion of Science for an Invitation Fellowship for Research that supported a visit to Nagoya University in the fall of 2015.
Group:Graduate Aeronautical Laboratories (Fluid Mechanics), GALCIT
Funders:
Funding AgencyGrant Number
Japan Society for the Promotion of Science (JSPS)UNSPECIFIED
Subject Keywords:detonation, propulsion, RDE
Record Number:CaltechGALCITFM:2017.001
Persistent URL:http://resolver.caltech.edu/CaltechGALCITFM:2017.001
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:81786
Collection:CaltechGALCITFM
Deposited By: Joseph Shepherd
Deposited On:25 Sep 2017 18:20
Last Modified:25 Sep 2017 18:20

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