摘要 |
<p>A gas turbine combustor is provided. The gas turbine combustor has a pilot nozzle having a pilot fuel injection port at a downstream end, in terms of the direction flow of a fuel, and lies on the axial centreline of the gas turbine combustor. It also has a main combustion zone, downstream of the pilot nozzle, and a pilot cone projecting from the vicinity of the pilot fuel injection port and having a diverged end adjacent to the main combustion zone, wherein a half angle of the pilot cone is increasing in the downstream direction.</p> |
申请人 |
SIEMENS AKTIENGESELLSCHAFT;BARVE, VINAYAK;HUTH, MICHAEL;LANDRY, KYLE L.;WEGNER, BERNHARD |
发明人 |
BARVE, VINAYAK;HUTH, MICHAEL;LANDRY, KYLE L.;WEGNER, BERNHARD |