Abstract: A fuel injector for a fuel spray nozzle of a gas turbine engine combustor is provided. The fuel injector has an annular flow passage which conveys fuel to a prefilming lip at an end of the flow passage. The fuel injector also has plurality of fuel distributor slots which are circumferentially spaced around and in fluid communication with the other end of the flow passage to deliver respective fuel streams into the flow passage. The slots are configured so that the fuel streams enter the flow passage at a swirl angle of at least 80° relative to the axis of the flow passage.

Abstract: An ejector, which finds particular application as a fuel injector for a gas turbine engine, has an axially located passage ending as a nozzle having an internal surface facing radially inwardly towards the axis and which extends as an outboard cone about the axis of the passage and which terminates at a tip. The cone has a profile which replicates the unconstrained trajectory of the fuel leaving the passage. The outer surface of the ejector has a profile for accelerating a gaseous flow over the outer surface. Atomisation of fuel is improved along with relight capability, flame extinction and smoke production.