Patent ID: 7434401

Claim:
A fuel/air premixer for a gas turbine combustor, wherein: an airblast atomizer nozzle comprising a liquid film-forming body, a tubular inner surface of which serves as a fuel liquid film-forming surface, is disposed at an inlet portion to a tubular premixing tube as fuel atomizing means; a flow-deflecting tubular body having an annular cross section is disposed on the inside of and coaxially with said liquid film-forming body; a first air swirler is disposed in an upstream portion of an annular passage formed between an outer peripheral surface of said flow-deflecting tubular body and said liquid film-forming surface of said liquid film-forming body; a second air swirler is disposed in an upstream portion of a passage which comprises as a wall surface an inner peripheral surface of said flow-deflecting tubular body, said flow-deflecting tubular body takes a form in which an outer diameter defining said outer peripheral surface increases toward a tip end of said annular passage, and an inner diameter defining said inner peripheral surface has a minimum downstream of a downstream end of said second air swirler, and then increases toward the tip end of said passage; and a third air swirler is disposed on the outside of said liquid film-forming body in an upstream portion of an annular passage which comprises as a wall surface an inner peripheral surface of said premixing tube.