| 摘要 |
<p>PROBLEM TO BE SOLVED: To provide new combustion technology for gas turbine operation with multi-fuel combustion capability, low emissions of NOand CO and high thermal efficiency.SOLUTION: In a first combustion chamber (1), a premixed fuel air mixture is combusted in a stable flame at an average flame temperature in the range between 1400 K and 1800 K. At the downstream end of the first combustion chamber (1), additional air (9) is injected into a hot gas flow in order to reduce the temperature to a temperature below 1400 K. Additional fuel (10) is injected downstream of the injection site of the air (9), thereby generating a mixture of exhaust gas, air and fuel with auto-ignition time between 1 ms and 10 ms. The mixture enters a deflection unit (2) and is deflected there at least in a circumferential direction. In a sequential combustion chamber (3), the mixture is burned by auto-ignition and/or a combination of auto-ignition and recirculation of hot reaction products.</p> |
