Gas turbines preliminary mixer with crater like fuel injection points

摘要

A preliminary mixer for a gas turbine combustion chamber contains a swirler (12), which a plurality of deflection blades (14), which contains an air flow through the preliminary mixer of imparting a swirl velocity, and at least one fuel injection point (16), the mixing of fuel with the air flow in the preliminary mixer allows. The fuel injection location ends in a crater like hole (32). The crater-like hole increases the mixing efficiency and increases the resistance against flashback / flame holding.