Fuel injector for a gas turbine engine

A fuel injector for a gas turbine engine comprising a compression section, a combustion section, and a turbine section in serial flow arrangement, the fuel injector comprising:

• an outer wall surrounding an injector passage and defining a longitudinal injector axis, the injector passage exhausting at an injector outlet and defining a flow direction through the injector passage;
• a first converging portion provided in the outer wall;
• a swirler assembly configured to provide a swirled airflow to the injector passage upstream of the first converging portion relative to the flow direction;
• a set of fuel passages in annular arrangement about the outer wall and fluidly exhausting to the injector passage downstream of the first converging portion relative to the flow direction;
• an annular body positioned within the injector passage along the outer wall upstream of the set of fuel passages relative to the flow direction, the annular body including a forward surface, an aft surface aligned with the set of fuel passages, and a side surface;
• and
• a set of flow passages extending through the annular body and configured to exhaust air from the side surface to energize a bluff region downstream of the set of fuel passages.