A combustor for providing homogeneous combustion of liquid fuels includes an essentially tube shaped combustion body, including a combustion chamber having a plurality of reaction zones, one of which is an injection zone, the others being combustion zones for staged homogeneous combustion of evaporated fuel and air. A swirler, including a base and swirler elements, is configured to operate at a swirl number between 0.6-2.5 in combination with a flow constriction plate whose size is such that the ratio of the open diameter (De) of the constriction to the diameter (D) of the combustion body is <0.7 and the constrictor plate is placed at a distance (L1) from the base of the swirler base so that L1/De>1. A primary mixing plate is placed downstream from the constriction plate at a distance (L2) so that the ratio L2/L1<1 to allow maximum mixing of the homogeneous combustion.

A fuel combustion system comprises a discharge nozzle with concentric fuel and air orifices. A fuel conduit is coupled to each fuel orifice for supplying liquid fuel thereto. An air conduit is coupled to each air orifice for supplying air thereto. The fuel and the pressurized air only mixing with one another, upon being discharged from the respective fuel and air orifices, to form a fuel mixture. A supplemental air source supplies supplement air to facilitate combustion. An air deflector sleeve at least partially surrounds and accommodates the at least one discharge nozzle and a cylindrical blast tube surrounding the air deflector sleeve and an outlet end of the cylindrical blast tube supports a flame retention head. The flame retention head redirects the supplement air radially inward, through openings in the air deflector sleeve and the flame retention head, to assist with combustion of the fuel mixture.

A burner includes a generally cylindrical reactor chamber (1) including a housing (1) having a proximal end (1p) and a distal end (1d). In the distal end of the reactor chamber (1) there is provided a catalyst (4). A fuel inlet (7) is provided in the proximal end of the reactor chamber. There are also a plurality of air inlets (22, 23; 24) arranged in the reactor wall at the proximal end. The inlets are configured to provide a rotating flow of the air injected into the reactor chamber. There is also provided a flow homogenizer (8; 30) extending over the cross-section of the reactor chamber at a position between the fuel inlet (7) and the catalyst (4).

A fuel nozzle for use in a turbine engine is provided. The fuel nozzle includes at least one premixer tube including a tube wall and a plurality of perforations defined therein and extending through the tube wall. The plurality of perforations are configured to channel a flow of air therethrough. The fuel nozzle also includes a liquid fuel plenum positioned upstream from the premixer tube, and at least one fuel injector coupled in flow communication with the liquid fuel plenum and the at least one premixer tube. The at least one fuel injector is configured to channel a flow of liquid fuel from the liquid fuel plenum into the premixer tube.

A fuel-fired burner includes a combustion air inlet for receiving combustion air coupled to a combustion air nozzle at an input to a second chamber within a burner housing spaced apart from a third chamber within the second chamber. The combustion air nozzle directs the combustion air into the third chamber. A fuel inlet coupled to a burner nozzle secured to a burner mounting plate has a recycle port for receiving hot exhaust gas provided to an exhaust gas path. A jet pump located entirely inside the burner housing is configured to receive the hot exhaust gas from the exhaust gas path. The jet pump operates by flowing the combustion air through the combustion air nozzle which suctions in the hot exhaust gas through the recycle port into the exhaust gas path then into a gas mixing zone for mixing the hot exhaust gas and the combustion air.