Reaction Systems Inc.

Tda Research, Inc.

Bradley Dean Hitch

David Thomas Wickham

Jeffrey Robert Engel

Jacquelyn Brett Lewis

Michael D Diener

J Michael Alford

James Nabity

A NO 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. NO decomposition is an exothermic reaction and produces a high temperature product containing high concentrations of O. 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 COand NO, 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. and it is desirable that the effluent temperature remains within this range for periods of up to two minutes.

Transient NO decomposition process and reactor

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.

Decahydronaphthalene as an endothermic fuel for hypersonic vehicles

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.

The present invention provides a combustion apparatus for the production of carbon nanomaterials including fullerenes and fullerenic soot. Most generally the combustion apparatus comprises one or more inlets for introducing an oxygen-containing gas and a hydrocarbon fuel gas in the combustion system such that a flame can be established from the mixed gases, a droplet delivery apparatus for introducing droplets of a liquid hydrocarbon feedstock into the flame, and a collector apparatus for collecting condensable products containing carbon nanomaterials that are generated in the combustion system. The combustion system optionally has a reaction zone downstream of the flame. If this reaction zone is present the hydrocarbon feedstock can be introduced into the flame, the reaction zone or both.

Growing community of inventors

Golden, CO, United States of America

Bradley Dean Hitch