| 摘要 |
<p>The invention provides a new path of combustion technology for gas turbine operation with multifuel capability, low emissions of NO x and CO and high thermal efficiency. According to the present invention a method for operating a combustor for a gas turbine and a combustor for a gas turbine are disclosed, at least comprising a first combustion chamber 1 with a wide operating range, a subsequent deflection unit 2 for deflecting the hot gas flow of the first combustion chamber 1 at least in circumferential direction and including components 11, 12, 13, 14 for injecting and mixing additional air 9 and/or fuel 10, and a sequential combustion chamber 3 with a short residence time, where the temperature of the hot gases reaches its maximum.</p> |
