Patent ID: 7546734

Claim:
A fuel injection device for a gas turbine, comprising: an airflow passage having an outer annular wall, a main stream of the airflow through the fuel injection device passing through the airflow passage within the outer annular wall, an air swirler positioned to swirl the main stream of the airflow and which thereby creates a high local air mass flow positioned at a radially outward portion of the main stream of the airflow near the outer annular wall, a plurality of fuel openings positioned on the outer annular wall of the airflow passage, downstream of the air swirler, for the injection of liquid fuel into the main stream of the airflow, wherein, a center axis of each fuel opening is inclined in a circumferential direction and also inclined axially against the main stream of the airflow such that the liquid fuel is injected radially inwardly, axially upstream and with a circumferential component to a controlled penetration depth within the high local air mass flow.