Abstract: The liner cap assembly includes an outer tubular sleeve, an inner cowl and a cone portion extending between the outer sleeve and the inner cowl. The cone portion includes a plurality of annular, concentrically arranged directional vanes on a downstream surface of the cone portion. At least the inner cowl and the cone portion are formed by casting. Plural apertures are formed in the cone portion during casting or after casting.

Abstract: A single nozzle combustion liner cap assembly is provided in the form of an outer annular sleeve connected to an inner center ring or cowl by an angled web or cone portion formed with multiple arrays of holes for introducing air through the cone portion where it is then diverted in desired directions by cooling slots formed by integral baffles or vanes formed on the downstream side of the cone portion. In one exemplary embodiment, three baffles or directional vanes are provided on the cone portion, the two innermost of which direct air radially inwardly along the downstream surface of the cone toward the cowl, and the third of which directs air in two opposite directions, i.e., inwardly and outwardly along the cone portion.

Abstract: An air admission insert particularly adapted for air admission holes in a combustor liner in a gas turbine combustion system comprises a pair of sleeve members, one of which is inserted in the other in axial but eccentric relationship so that the sides of the sleeves contact each other with the intervening space between the sleeves being crescent shaped. The insert is positioned concentrically in a combustor liner air admission hole. Combustion air flows through the insert and into the combustor liner and axially through the crescent space to cool the insert as well as the liner hold perimeter.

Abstract: A nozzle is provided for a gas turbine combustion system in which the atomizing air metering nozzle is provided with an aerodynamically rotating orifice which turns air flow radially inward toward the source of oil or other liquid fuel prior to initiating a swirling vortex to eliminate centrifuging action of the air stream within the nozzle. Metering on the atomizing air vortex generating vanes are located at the exit of the vanes near the outer face of the fuel nozzle to eliminate entrapment of airborne particles. Vortex generator vanes are provided in the air stream path; these vanes lie on the surface of a cone which converges toward the nozzle exit. The vanes are at an angle to lines which would lie in a plane through the axis of the aforementioned cone along the surface of the cone, thereby to form a swirling air vortex at the nozzle exit.