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A photon ignition system for igniting the air/fuel spray within a combustion chamber of a gas turbine engine is comprised of a photon source 20, a photon transmission means 22 and a focussing means 24. The source 20 has an output wavelength characteristic suitable for being absorbed by the hydrocarb

A photon ignition system for igniting the air/fuel spray within a combustion chamber of a gas turbine engine is comprised of a photon source 20, a photon transmission means 22 and a focussing means 24. The source 20 has an output wavelength characteristic suitable for being absorbed by the hydrocarbon fuel droplets within the fuel spray. In accordance with one embodiment of the invention the source 20 comprises an ultraviolet flashlamp having spectral characteristics which are selected to be strongly absorbed by hydrocarbon fuel. In another embodiment of the invention the source 20 comprises a laser, such an excimer laser, having an output pulse with wavelengths within the strong absorption range of hydrocarbon fuel. The photon output of the source 20 is focussed within an optimum region of the fuel spray for igniting one or more droplets therein due to the absorption and subsequent heating of the droplets of the focussed photon output.

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1. A method of igniting a hydrocarbon fuel comprised of droplets of hydrocarbon fuel, comprising the steps of: providing the hydrocarbon fuel as an air/fuel spray comprised of droplets of hydrocarbon fuel; generating electromagnetic energy having one or more wavelengths primarily within a range

1. A method of igniting a hydrocarbon fuel comprised of droplets of hydrocarbon fuel, comprising the steps of: providing the hydrocarbon fuel as an air/fuel spray comprised of droplets of hydrocarbon fuel; generating electromagnetic energy having one or more wavelengths primarily within a range of approximately 185 nm to approximately 400 nm; and directing the energy into the air/fuel spray such that one or more droplets absorb the energy and are heated, fragmented and ignited thereby. 2. A method as defined in claim 1 wherein the step of providing includes a step of generating a spray of hydrocarbon fuel with one or more fuel injectors. 3. A method as defined in claim 1 wherein the step of generating electromagnetic energy includes a step of pulsing an electromagnetic energy source. 4. A method as defined in claim 1 wherein the step of directing further includes the steps of: directing the energy into a transmission means operable for transmitting the energy to the fuel; and focussing the energy such that the energy is focussed within a desired region within the fuel. 5. A method as defined in claim 4 wherein the desired region is a region wherein ignition of the fuel occurs with a minimum required amount of power of generated electromagnetic energy relative to other regions within the fuel. 6. A method of igniting a hydrocarbon fuel/air spray within a combustion chamber of a gas turbine engine, comprising the steps of: activating a source of electromagnetic energy to produce a radiant energy output, the radiant energy output having a wavelength or wavelengths primarily within a range of approximately 185 nm to approximately 400 nm; and directing the output into a hydrocarbon fuel/air spray within the combustion chamber, the hydrocarbon fuel being comprised of hydrocarbon fuel droplets, such that one or more of the droplets absorb the radiant energy, the droplet or droplets absorbing the output energy being heated, fragmented and ignited. 7. A method as defined in claim 6 wherein the step of directing further comprises the steps of: transmitting the radiant energy from the source to the combustion chamber; and focussing the radiant energy at a predetermined spatial position within the spray. 8. A method as defined in claim 7 wherein the step of focussing includes a step of providing a focussing means disposed adjacent the combustion chamber. 9. A method as defined in claim 7 wherein the predetermined spatial position is a position for igniting the spray with a minimum required radiant energy output of the source relative to other positions within the spray. 10. A method as set forth in claim 6 wherein the step of activating activates a laser to produce laser radiation. 11. A method as defined in claim 10 wherein the step of directing is accomplished by transmitting a pulse of laser radiation through an optical transmission means. 12. A method as defined in claim 6 wherein the step of activating activates a flashlamp to produce a pulse of radiant energy. 13. A method as defined in claim 12 wherein the step of activating a flashlamp is accomplished by activating an ultraviolet enhanced flashlamp having a characteristic range of wavelengths within the range of approximately 180 nm to approximately 400 nm. 14. A photon ignition system for igniting a fuel spray comprised of droplets of hydrocarbon fuel within a combustion chamber of a gas turbine engine comprising: means for generating a source of photons having a wavelength or wavelengths primarily within a predetermined range of wavelengths of approximately 185 nm to approximately 400 nm; means for transmitting the photons from said generating means to a combustion chamber within a gas turbine engine; and means for directing the photons to a predetermined region within a fuel spray within the combustion chamber, the spray comprising droplets of hydrocarbon fuel, the hydrocarbon fuel droplets within the predetermined region absorbing the photons and being heated, fragmented and ignited thereby. 15. A system as defined in claim 14 wherein said means for transmitting comprises an optical fiber. 16. A system as defined in claim 15 wherein said means for directing comprises an optical focussing means disposed between an output end of said fiber and the spray for focussing the photons within the predetermined region of the spray. 17. A system as defined in claim 15 wherein said means for directing is a terminal portion of said fiber, said terminal portion of said fiber having a radially varying index of refraction being operable for optically focussing the photons within a desired region of the spray. 18. A system as defined in claim 14 wherein said means for generating comprises a flashlamp operable for generating a pulsed photon output having wavelengths within said predetermined range of wavelengths. 19. A system as defined in claim 14 wherein said means for generating is a laser operable for generating a photon output having a wavelength or wavelengths within said predetermined range of wavelengths. 20. A gas turbine engine photon ignition system for igniting an air/fuel spray comprised of hydrocarbon fuel droplets within a combustion chamber of a gas turbine engine, comprising: a source of photons, said photons having a characteristic wavelength or wavelengths primarily within a range of approximately 185 nm to approximately 400 nm, the absorption of the photons by the hydrocarbon fuel droplets inducing a heating, fragmentation and ignition of the fuel droplets; photon transmission means being operable for transmitting the photons from the source to the combustion chamber; and focussing means operable for focussing the transmitted photons within the combustion chamber for igniting the fuel droplets within the air/fuel spray. 21. A system as defined in claim 20 wherein said focussing means focusses the photons through an opening made through a housing which encloses the combustion chamber. 22. A system as defined in claim 20 wherein said focussing means is provided within a fuel injector of the combustion chamber, said focussing means being operable for focussing the photons at a region defined by the air/fuel spray emanating from said fuel injector. 23. A system as defined in claim 20 wherein said source of photons comprises a flashlamp system. 24. A system as defined in claim 20 wherein said source of photons comprises a laser system. 25. A system as defined in claim 20 wherein the combustion chamber is provided with a plurality of photon ignition systems. 26. A method of igniting a fuel spray within a combustion chamber of a gas turbine engine, the fuel spray being comprised of droplets of hydrocarbon fuel, comprising the steps of: generating a pulse of electromagnetic energy having wavelengths primarily within a range of wavelengths between approximately 185 nm to approximately 400 nm; directing the pulse such that it contacts one or more of the droplets within the fuel spray; and absorbing within at least one droplet the energy of the pulse for inducing a thermal gradient within the droplet such that one or more internal regions of the droplet have a temperature which exceeds the vapor temperature of the hydrocarbon fuel, the temperature being of sufficient magnitude to rupture the surface of the droplet such that hydrocarbon fuel vapor is released and the droplet is fragmented into smaller droplets and free electrons resulting in an ignition of the droplet. 27. A method as defined in claim 26 wherein the step of generating is accomplished by activating a flashlamp. 28. A method as defined in claim 26 wherein the step of generating is accomplished by activating a laser. 29. In a system having one or more gas turbine engines for providing power thereto, each of the engines comprising a combustion chamber wherein an air/fuel spray is ignited, the fuel comprising a hydrocarbon fuel, a method of igniting the air/fuel spray within each of the combustion chambers comprising the steps of: activating at least one source of electromagnetic energy to produce a radiant energy output, the radiant energy output comprising a wavelength or wavelengths primarily within a range of approximately 185 nm to 400 nm; and directing the output into the air/fuel spray within each of the combustion chambers, the spray being comprised of hydrocarbon fuel droplets, such that one or more of the droplets absorb the radiant energy and are heated, fragmented and ignited thereby. 30. A method as defined in claim 29 wherein the system is an aircraft and wherein the step of activating is accomplished in a repetitive fashion during the takeoff and landing of the aircraft. 31. A method as defined in claim 29 wherein the system is an aircraft and wherein the step of activating is accomplished in a repetitive fashion during the takeoff, flight and landing of the aircraft. 32. A method as defined in claim 29 wherein the step of activating is accomplished during the initial starting and also during the operation of each of the engines whereby the probability of loss of power from one or more of the engines due to a loss of combustion within the engine is substantially eliminated. 33. A photon ignition system for igniting a hydrocarbon fuel spray within a combustion chamber of a gas turbine engine, the photon ignition system comprising: means for generating a source of photons having a wavelength or wavelengths primarily within a range of wavelengths of approximately 185 nm to approximately 400 nm; optical fiber means for transmitting the photons from said generating means to the combustion chamber; and focussing means optically coupled to an end of said optical fiber means for directing the photons to at least one air/fuel spray emanating from at least one fuel injector within the combustion chamber, the air/fuel spray being comprised of a plurality of hydrocarbon fuel droplets, the fuel droplets having a wavelength absorption characteristic for absorbing the photons such that the droplets are heated to an ignition temperature whereby the air/fuel spray is ignited. 34. A system as defined in claim 33 wherein said means for directing is a terminal portion of said fiber, said terminal portion of said fiber having a radially varying index of refraction being operable for optically focussing the photons within a desired region of the fuel. 35. A system as defined in claim 33 wherein said means for generating comprises a flashlamp operable for generating a pulsed photon output having wavelengths within said predetermined range of wavelengths. 36. A system as defined in claim 33 wherein said means for generating is a laser operable for generating a photon output having a wavelength or wavelengths within said predetermined range of wavelengths. 37. A system as defined in claim 33 wherein said means for generating comprises a laser means operable for generating a photon output having wavelengths within said predetermined range of wavelengths.