COMBUSTOR BURNER ARRANGEMENT

摘要

A burner 30 for a combustor 56 of a gas turbine combustor 16 comprises a body 53 having a surface 64 and a burner axis 50, a fuel lance 56, an igniter 58 and a main air flow passage 62 or passages 62. The main air flow passage 62 or passages 62 is angled relative to the burner axis 50 and creates a main vortex 34C about the burner axis 50 in a first rotational direction, the main vortex travels in a direction along the burner axis 50 and away from the surface 64. The fuel lance 56 is located downstream of the igniter 58 with respect to the first rotational direction of the main vortex so that a part of a main air flow 34A washes over the fuel lance 56 and then over the igniter 58. The fuel lance 56 comprises a fuel lance axis 79, a liquid fuel tip 72 having a fuel outlet 86 and an array of air assist passages 88 having outlets 90 arranged about the fuel outlet 86. The air assist passages 88 are angled relative to the fuel lance axis 79 to create an air assist vortex about the fuel lance axis 79 in the same rotational direction to the first rotational direction.