Abstract: An annular combustor having radial dilution air injection in a gas turbine is disclosed. The gas turbine includes a rotor having turbine blades and a nozzle adjacent the turbine blades which is adapted to direct hot gases at the turbine blades to cause rotation of the rotor. The annular combustor is disposed about the rotor and has an outlet to the nozzle, spaced inner and outer walls, and a generally radially extending wall connecting the inner and outer walls. The gas turbine includes a housing substantially surrounding the annular combustor in spaced relation to the inner, outer and radially extending walls to define a dilution air flow path. The dilution air flow path includes a compressed air inlet in communication with a compressor supplying dilution air at one end thereof and a compressed air outlet in communication with the annular combustor adjacent the outlet at the other end thereof.

Abstract: A spray nozzle including a body having a fluid inlet at one end thereof and an exit orifice at the other end thereof. The fluid inlet communicates with the exit orifice through a fluid flow path extending through the body. The exit orifice is adapted to atomize the fluid as the fluid leaves the body. The spray nozzle also includes a separate portion for atomizing the fluid independent of the exit orifice. The separate portion communicates with the fluid flow path upstream of the exit orifice. The separate portion produces a flat spray of the fluid as the fluid leaves the body. With these features, the spray nozzle is well suited as a fuel injector for a gas turbine.