Patent ID: 9719419
Date: 2017-08-01
CPC Classifications: F02C,F23R

Claim:
1. A gas turbine combustor comprising: an external cylinder; an inner cylinder provided inside the external cylinder to form an air passage between the external cylinder and the inner cylinder; a pilot nozzle provided in a center part of the inner cylinder along a direction of a combustor axis; a plurality of main nozzles provided on an inner peripheral surface of the inner cylinder along a circumferential direction thereof so as to surround the pilot nozzle, wherein the plurality of main nozzles are arranged to premix fuel with combustion air introduced to the air passage and eject the fuel into the inner cylinder; and a plurality of top hat nozzles provided inside the air passage and including a plurality of fuel ejection ports, from which the fuel is ejected, across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles, wherein the plurality of top hat nozzles are aligned on an axial plane perpendicular to the direction of the combustor axis, and wherein, with respect to every pair of circumferentially adjacent fuel ejection ports of the plurality of fuel ejection ports, the circumferentially adjacent fuel ejection ports of the plurality of fuel ejection ports have different axial positions along the combustion axis direction from each other.