Patent ID: 9388985
Filing Date: 2016-07-12
CPC Classification: F05B,F23R

Claim Text:
1. A premixing apparatus for a gas turbine combustor, the premixing apparatus comprising: a fuel inlet configured to receive fuel and direct the fuel into the premixing apparatus; a swirl assembly at a center of a face of the premixing apparatus, the swirl assembly including swirl vanes, wherein each of the swirl vanes includes a fuel injection port in fluid communication with the fuel inlet and through which fuel is delivered from the fuel injection port to mix the fuel with oxidant flowing around the swirler vanes to produce a first fuel/oxidant mixture which flows to a combustion chamber for combustion; and non-swirl elements surrounding the swirl assembly, each non-swirl element comprising a respective micromixer including a group of tubes arranged in a respective tube bundle, each respective tube bundle having tubes relatively closely spaced from one another as compared to a spacing from tubes of another tube bundle, wherein each micromixer is in fluid communication with the fuel inlet and fuel and oxidant are premixed within each tube to produce a second fuel/oxidant mixture flowing from the non-swirl elements to the combustion chamber for combustion.