Design and testing of a small-scale laboratory rotating detonation engine running on ethylene-oxygen
Design and testing of a small-scale laboratory rotating detonation engine running on ethylene-oxygen
A modular laboratory rotating detonation engine (RDE) for combined mass flowrates below 10 g/s has been designed. Since a large chamber diameter to width ratio is used, first tests with stoichiometric ethylene-oxygen mixtures have revealed detonation modes with one, two and three separate detonation heads, depending on mass flow rate. Spectrograms from high-frequency pressure data and high-speed photography are used to confirm successful operation and identify the number of separate detonation fronts reliably. Measurements show that thrust increases by more than a factor 2 can be achieved by placing a constrictor nozzle at the exit of the cylindrical RDE outlet and adding an aerospike nozzle to the overall engine design.
American Institute of Aeronautics and Astronautics
Law, Hamilton
2a4400cf-b5eb-4754-a674-63b88bea0aae
Baxter, Tom
af5baf2c-29ab-45f2-bd67-61fac6510ebd
Ryan, Charles
3627e47b-01b8-4ddb-b248-4243aad1f872
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
28 July 2021
Law, Hamilton
2a4400cf-b5eb-4754-a674-63b88bea0aae
Baxter, Tom
af5baf2c-29ab-45f2-bd67-61fac6510ebd
Ryan, Charles
3627e47b-01b8-4ddb-b248-4243aad1f872
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Law, Hamilton, Baxter, Tom, Ryan, Charles and Deiterding, Ralf
(2021)
Design and testing of a small-scale laboratory rotating detonation engine running on ethylene-oxygen.
In AIAA Propulsion and Energy Forum and Exposition.
American Institute of Aeronautics and Astronautics.
15 pp
.
(doi:10.2514/6.2021-3658).
Record type:
Conference or Workshop Item
(Paper)
Abstract
A modular laboratory rotating detonation engine (RDE) for combined mass flowrates below 10 g/s has been designed. Since a large chamber diameter to width ratio is used, first tests with stoichiometric ethylene-oxygen mixtures have revealed detonation modes with one, two and three separate detonation heads, depending on mass flow rate. Spectrograms from high-frequency pressure data and high-speed photography are used to confirm successful operation and identify the number of separate detonation fronts reliably. Measurements show that thrust increases by more than a factor 2 can be achieved by placing a constrictor nozzle at the exit of the cylindrical RDE outlet and adding an aerospike nozzle to the overall engine design.
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Accepted/In Press date: 8 July 2021
Published date: 28 July 2021
Identifiers
Local EPrints ID: 450352
URI: http://eprints.soton.ac.uk/id/eprint/450352
PURE UUID: 95d721f9-0e96-4936-805d-119984bdc8e8
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Date deposited: 23 Jul 2021 18:13
Last modified: 17 Mar 2024 03:39
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Author:
Hamilton Law
Author:
Tom Baxter
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