GAS TURBINE PREMELANGER WITH FUEL INJECTION SITES IN CRATER

摘要

A premixer for a gas turbine combustor includes a turbulence device (12) including a plurality of curved blades (14) imparting a swirl rate to a flow of air passing through the premixer and at least one fuel injection (16) for mixing the fuel with the air flow in the premixer. The fuel injection site ends with a crater hole (32). The crater hole improves the mixing efficiency and increases the flameback / flame stabilization resistance.