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Heat Transfer Measurements of NASA Liquid Kerosene/Oxygen Rotating Detonation Rocket EngineThe RDRE has been identified as a viable high performance propulsion system with numerous advantages over the state-of-the-art (SOA) liquid rocket engine. NASA has been investigating this combustion device for applications ranging from lander, upper stage, thruster, and hypersonics. All of the activities funded to date have been focused on closing major technology gaps preventing the RDRE from being used more broadly by industry. One of those gaps include the prediction and management of heat transfer to the walls from the extreme combustion environment. This work overviews the heat transfer measurements made using new and existing hardware. A liquid oxygen / liquid RP-1 RDRE was tested utilizing a calorimeter outer body and outer body nozzle extension. An actively cooled inner body with axial running cooling channels was also used. A bimetallic GRCop-42 / Monel K500 injector was developed and demonstrated to be a viable technology for RDRE environments. Trends in bulk heat loads are discussed along with a direct comparison to constant pressure theory predictions of wall heat transfer. The experimental data obtained in this investigation showed similar heat fluxes to constant pressure theory indicating deflagration may have dominated the flow field. Only a single detonation wave was observed in all tests which imparted a significant dynamic load (vibration) on the test article making measurement of combustor performances extremely challenging. Both accelerometer and load cell data corroborate the extreme G-forces measured. The single wave mode yielded relatively low performances compared with other hot fire test data sets available. This leads to the conclusion that a single detonation wave in this geometry is not sufficient for high performance. Wave multiplicity, or rather, a specific number of waves may yield higher performances.
Document ID
20240015029
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Thomas Teasley
(Marshall Space Flight Center Redstone Arsenal, United States)
Dillon Petty
(Marshall Space Flight Center Redstone Arsenal, United States)
Michaela Hemming
(University of Alabama in Huntsville Huntsville, United States)
David Scarborough
(Auburn University Auburn, Alabama, United States)
Stephen Heister
(Purdue University West Lafayette West Lafayette, United States)
Date Acquired
November 24, 2024
Subject Category
Spacecraft Propulsion and Power
Meeting Information
Meeting: AIAA SciTech Forum and Exposition
Location: Orlando, FL
Country: US
Start Date: January 6, 2025
End Date: January 10, 2025
Sponsors: American Institute of Aeronautics and Astronautics
Funding Number(s)
WBS: 333098.07.01.04.62
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.
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