| 主权项 |
1. A burner for a combustor of a gas turbine combustor, the burner comprises comprising:
a body having a surface and an burner axis, a fuel lance, an igniter and a main air flow passage or passages, wherein the main air flow passage or passages is angled relative to the burner axis and creates a main vortex about the burner axis in a first rotational direction, the main vortex travels in a direction along the burner axis and away from the surface, wherein the fuel lance is located downstream of the igniter with respect to the first rotational direction of the main vortex so that a part of a main air flow washes over the fuel lance and then over the igniter, wherein the fuel lance comprises a fuel lance axis, a liquid fuel tip having a fuel outlet and an array of air assist passages having outlets arranged about the fuel outlet, wherein the air assist passages are angled relative to the fuel lance axis to create an air assist vortex about the fuel lance axis in the same rotational direction to the first rotational direction. |
