Single-circuit fuel injector for gas turbine combustors

A method of injecting fuel into a combustor, comprising:

• (a) providing a fuel injector;
• (b) flowing a central air stream over the fuel injector, the central air stream becoming axial downstream of the fuel injector and having no axial recirculation zone;
• (c) flowing a main air stream concentrically outside of the central air stream;
• (d) creating a bifurcated recirculation zone separating the central air stream from the main air stream;
• and
• (e) providing fuel to the fuel injector, during both a low power operating mode and a high power operating mode, through a single fuel supply path, fuel being supplied during the low power operating mode at a pressure within a first pressure range such that a majority of the fuel is entrained in the central air stream, and fuel being supplied during the high power operating mode at a pressure within a second pressure range, higher than the first pressure range, such that a majority of the fuel penetrates the central air stream and is entrained in the main air stream.