Abstract: Disclosed is an air-assisted simplex spray nozzle assembly for a fuel burner that includes, inter alia, a nozzle body that has opposed upstream and downstream ends, wherein the downstream end of the nozzle body defines a fuel outlet, an adapter member that is engaged with the upstream end of the nozzle body and defines concentrically positioned air and fuel inlets for the nozzle assembly and an air cap that is positioned over the downstream end of the nozzle body. The nozzle assembly further includes a fuel circuit and a first air circuit. The fuel circuit directs fuel from a fuel pump toward the fuel outlet of the nozzle body. The fuel circuit extends from the fuel inlet of the adapter member through the nozzle body to the fuel outlet. The first air circuit directs assist air towards the fuel exiting from the fuel outlet.

Abstract: An air-blast fuel injector is disclosed which includes an outer air circuit having an exit portion, an inner air circuit having an outlet configured to direct air toward the exit portion of the outer air circuit, and a fuel circuit radially outboard of the inner air circuit and having an exit communicating with the outer air circuit upstream from the exit portion of the outer air circuit.

Abstract: An air-blast fuel injector is disclosed which includes an outer air circuit having an exit portion, an inner air circuit having an outlet configured to direct air toward the exit portion of the outer air circuit, and a fuel circuit radially outboard of the inner air circuit and having an exit communicating with the outer air circuit upstream from the exit portion of the outer air circuit.

Abstract: An air-blast fuel injector is disclosed which includes an outer air circuit having an exit portion, an inner air circuit having an outlet configured to direct air toward the exit portion of the outer air circuit, and a fuel circuit radially outboard of the inner air circuit and having an exit communicating with the outer air circuit upstream from the exit portion of the outer air circuit.

Abstract: A lean direct injection fuel nozzle for a gas turbine is disclosed which includes a radially outer main fuel delivery system including a main inner air swirler defined in part by a main inner air passage having a radially inner wall with a diverging downstream surface, an intermediate air swirler radially inward of the main inner air swirler for providing a cooling air flow along the downstream surface of the radially inner wall of the main inner air passage, and a radially inner pilot fuel delivery system radially inward of the intermediate air swirler.

Abstract: A lean direct injection fuel nozzle for a gas turbine is disclosed which includes a radially outer main fuel delivery system including a main inner air swirler defined in part by a main inner air passage having a radially inner wall with a diverging downstream surface, an intermediate air swirler radially inward of the main inner air swirler for providing a cooling air flow along the downstream surface of the radially inner wall of the main inner air passage, and a radially inner pilot fuel delivery system radially inward of the intermediate air swirler.

Abstract: An air-blast fuel injector is disclosed that includes an on-axis inner air circuit, a fuel circuit radially outboard of the inner air circuit, the fuel circuit having an axially converging pre-filming chamber and an axially diverging pre-filming surface extending from the pre-filming chamber to an exit annulus and an outer air circuit radially outboard of the fuel circuit communicating with the exit annulus of the axially diverging pre-filming surface.

Abstract: An air-blast fuel injector is disclosed which includes an outer air circuit having an exit portion, an inner air circuit having an outlet configured to direct air toward the exit portion of the outer air circuit, and a fuel circuit radially outboard of the inner air circuit and having an exit communicating with the outer air circuit upstream from the exit portion of the outer air circuit.

Abstract: Disclosed is an air-assisted simplex spray nozzle assembly for a fuel burner that includes, inter alia, a nozzle body that has opposed upstream and downstream ends, wherein the downstream end of the nozzle body defines a fuel outlet, an adapter member that is engaged with the upstream end of the nozzle body and defines concentrically positioned air and fuel inlets for the nozzle assembly and an air cap that is positioned over the downstream end of the nozzle body. The nozzle assembly further includes a fuel circuit and a first air circuit. The fuel circuit directs fuel from a fuel pump toward the fuel outlet of the nozzle body. The fuel circuit extends from the fuel inlet of the adapter member through the nozzle body to the fuel outlet. The first air circuit directs assist air towards the fuel exiting from the fuel outlet.

Abstract: A fuel injector for a gas turbine is disclosed which includes a nozzle body having a discharge portion defining a discharge orifice, the discharge portion including a fuel circuit for directing a hollow fuel film toward the discharge orifice from a fuel pump associated with the gas turbine, and an air assist circuit for directing pressurized air from a source external to the gas turbine toward the fuel film upstream from the discharge orifice to impinge on an inner surface of the fuel film issuing from the discharge orifice.

Abstract: A fuel injector for a gas turbine is disclosed which includes a nozzle body having a discharge portion defining a discharge orifice, the discharge portion including a fuel circuit for directing a hollow fuel film toward the discharge orifice from a fuel pump associated with the gas turbine, and an air assist circuit for directing pressurized air from a source external to the gas turbine toward the fuel film upstream from the discharge orifice to impinge on an inner surface of the fuel film issuing from the discharge orifice.

Abstract: A fuel injector for a gas turbine is disclosed which includes a nozzle body having a discharge portion defining a discharge orifice, the discharge portion including a fuel circuit for directing a hollow fuel film toward the discharge orifice from a fuel pump associated with the gas turbine, and an air assist circuit for directing pressurized air from a source external to the gas turbine toward the fuel film upstream from the discharge orifice to impinge on an inner surface of the fuel film issuing from the discharge orifice.

Abstract: An igniter and fuel atomizer nozzle assembly in a gas turbine engine includes an igniter in which a fuel conduit is positioned in a passageway in the igniter between its housing and its electrode for discharging atomized start up fuel from the end of the igniter housing closely proximate to the ignition spark generated by the electrode.

Abstract: A simplex air blast fuel injection system for the atomization of fuel for ignition to drive a gas turbine includes a simplex nozzle which receives fuel from a fuel pump powered by the turbine over a range of pressures between maximum and minimum pressures during the operation of the turbine, and also receives fuel at a substantially lower pressure than the minimum fuel pressure when the turbine is cranked during startup. The fuel is discharged from the nozzle orifice as a swirling stream of atomized fuel during turbine operation, and as a film which is insufficiently atomized to initiate ignition during the turbine startup. An air compressor is also powered by the turbine to supply air at a low pressure to the fuel issuing from the nozzle orifice during both turbine operation and startup.

Abstract: A simplex air blast fuel injection system and method for the atomization of fuel for ignition to drive a gas turbine includes a simplex nozzle which receives a fuel from a fuel pump powered by the turbine over a range of pressures between maximum and minimum pressures during the operation of the turbine, and also received fuel from the fuel pump at a substantially lower pressure than the minimum fuel pressure when the turbine is cranked during startup. The fuel is discharged from the nozzle orifice as a swirling stream of atomized fuel during turbine operation, and as a film which is insufficiently atomized to initiate ignition during the turbine startup. An air compressor is also powered by the turbine to supply air at a low pressure and high volume to the fuel issuing from the nozzle orifice during both turbine operation and startup.