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In a method for igniting the combustion chamber of a gas turbine unit, a safely working ignition and a long lifetime of the ignition device (10) is achieved by discharging a compressed gas with a supercritical pressure ratio through a nozzle (21) and heating it up to a temperature sufficient to igni

In a method for igniting the combustion chamber of a gas turbine unit, a safely working ignition and a long lifetime of the ignition device (10) is achieved by discharging a compressed gas with a supercritical pressure ratio through a nozzle (21) and heating it up to a temperature sufficient to ignite hydrocarbons by interacting with a resonance tube (19) arranged behind said nozzle (21), and using said heated-up gas to directly or indirectly ignite a fuel/air mixture introduced into said combustion chamber.

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What is claimed is: 1. A method for igniting the combustion chamber of a gas turbine unit, the method comprising: discharging a compressed gas with a supercritical pressure ratio through a nozzle; heating up said compressed gas to a temperature sufficient to ignite hydrocarbons by interacting with

What is claimed is: 1. A method for igniting the combustion chamber of a gas turbine unit, the method comprising: discharging a compressed gas with a supercritical pressure ratio through a nozzle; heating up said compressed gas to a temperature sufficient to ignite hydrocarbons by interacting with a resonance tube arranged behind said nozzle; and using said heated-up gas directly or indirectly to ignite a mixture of air and a fuel, said fuel being introduced into said combustion chamber separately and simultaneously with said discharged compressed gas. 2. A method according to claim 1, wherein the combustion chamber comprises a combustion space to which a flame tube is connected that discharges into the combustion space; and comprising: introducing ignition fuel and ignition air into the flame tube; and igniting the ignition fuel/ignition air mixture in the flame tube. 3. A method according to claim 1, wherein the compressed gas comprises air. 4. A method according to claim 3, wherein an ignition space is arranged between the flame tube and the resonance tube that discharges into the flame tube; and comprising: supplying some of the air that is heated up in the resonance tube to the ignition space through an ignition opening in the resonance tube where said supplied air mixes with the ignition fuel and ignites. 5. A method according to claim 4, comprising: discharging the remainder of the air discharged into the resonance tube past the ignition space and into the flame tube. 6. A method according to claim 3, comprising: igniting the ignition fuel/ignition air mixture in the flame tube by contact with a heated-up surface of the resonance tube. 7. A method according to claim 3, comprising: using all the air discharged into the resonance tube to ignite the ignition fuel/ignition air mixture. 8. A method according to claim 3, comprising: using the combustion fuel of the gas turbine as ignition fuel. 9. A method according to claim 3, comprising: using a fuel other than the fuel of the gas turbine as ignition fuel. 10. A method according to claim 3, comprising: adding oxygen to improve the ignitability of the air that is heated up in the resonance tube, to improve the ignitability of the other air discharged into the resonance tube, or both. 11. A method according to claim 3, wherein the gas turbine unit comprises a compressor for compressing the combustion air, and comprising: taking the compressed air for igniting the combustion chamber from the compressor, from an external ignition air supply, or both. 12. A method according to claim 1, wherein the compressed gas to be used is not air; and comprising: using additional ignition air for ignition purposes; and heating up the additional ignition air. 13. A method according to claim 9, wherein said fuel other than the fuel of the gas turbine comprises methane or propane. 14. A method according to claim 12, wherein the compressed gas to be used comprises nitrogen. 15. An ignition device useful for igniting the combustion chamber of a gas turbine unit, the combustion chamber including a combustion space, the ignition device comprising: an ignition gas tube; a resonance tube; a nozzle configured and arranged to be supplied with compressed gas through the ignition gas tube, the resonance tube being arranged behind said nozzle and into which resonance tube gas from the nozzle can flow, the nozzle configured and arranged to be connected to the combustion chamber or the combustion space of the combustion chamber; an exit channel outside the resonance tube; a flame tube connected to the combustion space of the combustion chamber with the flame tube discharging into the combustion space; wherein at least some of the gas discharged through the nozzle into the resonance tube flows via the exit channel into the flame tube; an ignition space; wherein the resonance tube is adjacent to the ignition space; wherein the ignition space discharges into the flame tube; wherein the resonance tube comprises an ignition opening; and wherein part of the gas in the resonance tube exits the resonance tube through the ignition opening and flows directly into the ignition space. 16. An ignition device useful for igniting the combustion chamber of a gas turbine unit, the combustion chamber including a combustion space, the ignition device comprising: an ignition gas tube; a resonance tube; a nozzle configured and arranged to be supplied with compressed gas through the ignition gas tube, the resonance tube being arranged behind said nozzle and into which resonance tube gas from the nozzle can flow, the nozzle configured and arranged to be connected to the combustion chamber or the combustion space of the combustion chamber; an exit channel outside the resonance tube; a flame tube connected to the combustion space of the combustion chamber with the flame tube discharging into the combustion space; wherein at least some of the gas discharged through the nozzle into the resonance tube flows via the exit channel into the flame tube; a central fuel tube running to the flame tube; and wherein the ignition gas tube, the nozzle, and the resonance tube are arranged in series and parallel to the fuel tube. 17. An ignition device in accordance with claim 16, further comprising: a connecting channel connecting the resonance tube to the fuel tube.