Abstract: A burner construction for gas turbine engines in which the conventional throat is replaced by a plurality of tubes extending radially into the burner downstream of the end cap, the inner ends being spaced apart to provide a clear axial passage and the tubes being spaced apart circumferentially to leave axial passages therebetween.

Abstract: A burner construction for low emission burners in which the primary fuel is injected with air in an annulus into the upstream end of the burners so as to cause a significant recirculation of the fuel and air mixture adjacent to the end cap, the secondary fuel is injected into the burner in a small angle spray at a point substantially spaced from the end cap and large combustion and/or dilution holes in the burner wall a small distance upstream of the secondary nozzle are sized to produce an additional recirculation in the primary fuel and air around the secondary nozzle with this additional recirculation in the direction opposite to the first recirculation.

Abstract: A fuel injection system for low emission burners in which the primary fuel is delivered in an annular spray into the primary combustion zone; at high power operation, secondary fuel is injected additionally in a low angle axial spray to penetrate beyond the primary zone and into the secondary combustion zone downstream of the primary zone.

Abstract: In a two stage burner construction in which primary fuel burns in an annulus in a primary combustion zone and secondary fuel is discharged through the primary zone to a secondary zone downstream of the primary zone, vortex generators are used in the passage through which the fuel and air entering the primary zone to enhance the mixing and to improve the toroidal flow in the combustion zone. Other vortex generators are used to improve the mixing of the secondary fuel and air to improve secondary combustion. The vortex generators may be used in conjunction with a trip on the secondary nozzle tube to further enhance primary combustion.

Abstract: The performance of the diffuser action of burner shrouds is improved by establishing a substantially uniform velocity profile across the shroud passage by introducing a strong secondary flow in the form of vortices that lead to a better velocity profile and much improved diffuser action in the shroud passages.

Abstract: This invention is for a turbine type power plant which includes a swirl-type annular burner and is concerned with diverting a portion of compressor air from the compressor discharge flow stream where it is utilized for cooling and dilution in the burner and is particularly concerned with the construction of the diffuser section.

Abstract: An annular pilot combustor for a turbine type power plant includes radial inflow air and fuel nozzles judiciously oriented to improve heat load characteristics, eliminate a diffuser passage and shorten the overall combustor and supporting parts.