Abstract: A N2O decomposition reactor and a method of its use to produce an effluent suitable for use in an ignition device or in the main fuel injection system in high speed aircraft. N2O decomposition is an exothermic reaction and produces a high temperature product containing high concentrations of O2. Combination of fuel with this effluent ignites quickly and is an effective ignition source for the aircraft combustor. Reactor performance is adjusted to meet the conditions required for a selected application by changing the relative concentrations of CO2 and N2O, modifying the reactor length, and varying the quantity of catalyst in the reactor. For use in a pilot ignition device, the desired effluent temperature is between 500° C. and 1200° C. in order to ignite and combust the fuel within the design residence time, between 0.5 and 10 ms. For application as a barbotage gas generator in a fuel injection system, the temperature of the effluent can range from 300° C. up to 800° C.

Abstract: Endothermic fuel compositions comprising 50% or more by volume decahydronaphthalene, including cis-decahydronaphthalene, trans-decahydronaphthalene or a mixture thereof, for use as endothermic fuels in hypersonic vehicles and particularly for use in dual-mode ramjet or supersonic combustion ramjet air breathing engines. Methods for operating a ramjet or scram jet engine wherein the endothermic fuel is used for cooling the combustor and for combustion in the combustor.

Abstract: Endothermic fuel compositions comprising 50% or more by volume decahydronaphthalene, including cis-decahydronaphthalene, trans-decahydronaphthalene or a mixture thereof, for use as fuels in hypersonic vehicles and particularly for use in dual-mode ramjet or supersonic combustion ramjet air breathing engines.