Dual-Mode Combustion Experiments with an Integrated Aeroramp-Injector/Plasma-Torch Igniter
Abstract
Results from combustion experiments in a direct-connect supersonic combustor facility are presented. Successful ignition and sustained combustion of both hydrogen and ethylene fuels were achieved using an integrated aeroramp-injector/plasma-torch igniter configuration. A Mach 2 nozzle was used to obtain How simulating Mach approximate to 4 flight conditions at 27 km, at a total temperature of 1000 K and a static pressure of 42 kPa. Combustion was achieved at (global) equivalence ratios between 0.08 and 0.31 for hydrogen and 0.13 and 0.47 for ethylene, with corresponding maximum combustor pressure rises of about a factor of 4.0. One-dimensional performance analysis of the test data indicates combustion efficiencies as high as 75% for both fuels, in the leanest conditions tested. Off-design flight conditions were tested by varying the freestream air total temperature. Supersonic combustion was achieved at total temperatures as low as 530 K with hydrogen and 680 K with ethylene.
Additional Information
© 2007 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Received 10 October 2006; revision received 21 August 2007; accepted for publication 8 September 2007. This research was supported by the NASA Langley Research Center under Grant NAG-1-02108. The authors would like to acknowledge the help of L. Jacobsen in the design of the plasma torch and the help of R. Krauss in the operation of the supersonic combustion facility.Attached Files
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Additional details
- Eprint ID
- 106941
- Resolver ID
- CaltechAUTHORS:20201207-094042032
- NASA
- NAG-1-02108
- Created
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2020-12-07Created from EPrint's datestamp field
- Updated
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2021-11-16Created from EPrint's last_modified field