Patent ID: 6993916

Claim:
A burner for use in a combustion system of an industrial gas turbine, the burner comprising: an outer peripheral wall; a burner center body coaxially disposed within said outer wall; a fuel/air premixer including an air inlet, at least one fuel inlet, and a splitter ring, the splitter ring defining a first, radially inner passage, with respect to the axis of the center body, with the center body and a second, radially outer passage with the outer wall, the first and second passages each having air flow turning vanes which impart swirl to the combustion air passing through the premixer, said vanes connected respectively to said center body and said splitter ring and to said splitter ring and said outer wall; and a gas fuel flow passage defined within said center body and extending at least part circumferentially thereof, for conducting gas fuel to said fuel/air premixer.