Type of Document Dissertation Author Bonanos, Aristides Michael Author's Email Address email@example.com, firstname.lastname@example.org URN etd-09012005-141732 Title Scramjet Operability Range Studies of an Integrated Aerodynamic-Ramp-Injector/Plasma-Torch Igniter with Hydrogen and Hydrocarbon Fuels Degree PhD Department Aerospace and Ocean Engineering Advisory Committee
Advisor Name Title Schetz, Joseph A. Committee Chair Barnwell, Richard W. Committee Member Goyne, Christopher P. Committee Member O'Brien, Walter F. Jr. Committee Member Wang, Joseph J. Committee Member Keywords
- aeroramp mixing and injection
- hypersonic propulsion
- plasma torch
- supersonic combustion
Date of Defense 2005-08-22 Availability unrestricted AbstractAn integrated aerodynamic-ramp-injector/plasma-torch-igniter of original design was tested in a M∞ = 2, unvitiated, heated flow facility arranged as a diverging duct scramjet combustor. The facility operated at a total temperature of 1000 K and total pressure of 330 kPa. Hydrogen (H2), ethylene (C2H4) and methane (CH4) were used as fuels, and a wide range of global equivalence ratios were tested. The main data obtained were wall static pressure measurements, and the presence of combustion was determined based on the pressure rises obtained.
Supersonic and dual-mode combustion were achieved with hydrogen and ethylene fuel, whereas very limited heat release was obtained with the methane. Global operability limits were determined to be 0.07 < φ < 0.31 for hydrogen, and 0.14 < φ < 0.48 for ethylene. The hydrogen fuel data for the aeroramp/torch system was compared to data from a physical 10º unswept compression ramp injector and similar performance was found with the two arrangements. With hydrogen and ethylene as fuels and the aeroramp/plasma-torch system, the effect of varying the air total temperature was investigated. Supersonic combustion was achieved with temperatures as low as 530K and 680K for the two fuels, respectively. These temperatures are facility/operational limits, not combustion limits.
The pressure profiles were analyzed using the Ramjet Propulsion Analysis (RJPA) code. Results indicate that both supersonic and dual-mode ramjet combustion were achieved. Combustion efficiencies varied with φ from a high of about 75% to a low of about 45% at the highest φ. With a theoretical diffuser and nozzle assumed for the configuration and engine, thrust was computed for each fuel. Fuel specific impulse was on average 3000 and 1000 seconds for hydrogen and ethylene respectively, and air specific impulse varied from a low of about 9 sec to a high of about 24 sec (for both fuels) for the To = 1000K test condition.
The GASP RANS code was used to numerically simulate the injection and mixing process of the fuels. The results of this study were very useful in determining the suitability of the selected plasma torch locations. Further, this tool can be used to determine whether combustion is theoretically possible or not.
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