Patent ID: 9163838
Filing Date: 2015-10-20
Classification: F23C,F23D,F23R

Abstract:
1. A gas turbine combustion burner comprising a plurality of swirling vanes for ejecting fuel from fuel ejection holes into air or a mixture of air and fuel flowing from an upstream side while applying a swirling force to form a swirling mixed airflow and a nozzle having the swirling vanes arranged radially on an outer circumferential surface thereof and having a first fuel passage, through which the fuel is guided to the fuel ejection holes, is provided in the nozzle, wherein a cavity communicating with the fuel ejection holes is provided in each swirling vane, and at least two second fuel passages are provided between the cavity and the first fuel passage along an axial direction, and wherein a nozzle tip of the nozzle having a closed end.