TY - GEN
T1 - The auto-ignition of kerosene-based sythetic fuel/hydrogen peroxide propellants and its injector design
AU - Yuan, Tony
AU - Chen, Yu-Ta
AU - Zhou, Jing Yuan
PY - 2018/1/1
Y1 - 2018/1/1
N2 - The combination of kerosene with hydrogen peroxide is more promising due to its low cost, low toxicity, long storage capability, and adequate propulsive performance (Isp>280second, and C*>1400m/s). This research formulates a kerosene based fuel (W2) which shows hypergolic characteristics when in contact with hydrogen peroxide. W2 and hydrogen peroxide present an ignition delay time of 21ms in droplet contact test. The high heating value(ΔH=32.5kJ/g) fuel is prepared by combining several catalysts, promoted mediums, and kerosene to make miscible and hypergolic with hydrogen peroxide. Since the delay time is still long comparing to conventional hypergolic propellant systems, a premixed type bipropellant injector design, namely liquid-cyclonic injector unit has been designed to obtain auto-ignition capability. Liquid fuel and oxidizer are tangentially injected into the small chamber to mix and provide the period for liquid catalytic reaction and the formed hollow center space holds the vaporized propellant to perform gas-phase oxidation reactions to its autoignition temperature. In the hot-fire experiments, the auto-ignition behavor and the operation limits of injectors are also discussed.
AB - The combination of kerosene with hydrogen peroxide is more promising due to its low cost, low toxicity, long storage capability, and adequate propulsive performance (Isp>280second, and C*>1400m/s). This research formulates a kerosene based fuel (W2) which shows hypergolic characteristics when in contact with hydrogen peroxide. W2 and hydrogen peroxide present an ignition delay time of 21ms in droplet contact test. The high heating value(ΔH=32.5kJ/g) fuel is prepared by combining several catalysts, promoted mediums, and kerosene to make miscible and hypergolic with hydrogen peroxide. Since the delay time is still long comparing to conventional hypergolic propellant systems, a premixed type bipropellant injector design, namely liquid-cyclonic injector unit has been designed to obtain auto-ignition capability. Liquid fuel and oxidizer are tangentially injected into the small chamber to mix and provide the period for liquid catalytic reaction and the formed hollow center space holds the vaporized propellant to perform gas-phase oxidation reactions to its autoignition temperature. In the hot-fire experiments, the auto-ignition behavor and the operation limits of injectors are also discussed.
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U2 - 10.2514/6.2018-4775
DO - 10.2514/6.2018-4775
M3 - Conference contribution
SN - 9781624105708
T3 - 2018 Joint Propulsion Conference
BT - 2018 Joint Propulsion Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018
Y2 - 9 July 2018 through 11 July 2018
ER -