Abstract: A burner for use in a combustion system of a heavy-duty industrial gas turbine includes a fuel/air premixer having an air inlet, a fuel inlet, and an annular mixing passage. The fuel/air premixer mixes fuel and air into a uniform mixture for injection into a combustor reaction zone. The burner also includes an inlet flow conditioner disposed at the air inlet of the fuel/air premixer for controlling a radial and circumferential distribution of incoming air. The pattern of perforations in the inlet flow conditioner is designed such that a uniform air flow distribution is produced at the swirler inlet annulus in both the radial and circumference directions. The premixer includes a swozzle assembly having a series of preferably air foil shaped turning vanes that impart swirl to the airflow entering via the inlet flow conditioner.

Abstract: The dual-fuel nozzle for a gas turbine and combustor includes a liquid fuel nozzle surrounded by a gas fuel nozzle. A converging sleeve surrounds the converging outer wall of the combined liquid fuel and gaseous nozzle to form a duct of decreasing cross-sectional area in a downstream direction whereby air flow through the duct accelerates toward the conical droplet spray pattern emerging from the liquid fuel nozzle. An inside swirler is located upstream of the liquid fuel tip to swirl the air flowing through the duct. An outer swirler is provided about the downstream end of the sleeve, likewise to swirl air. The accelerated swirling air flow through the duct and outer swirling air flow preclude impingement of oil spray droplets onto metal surfaces of the nozzle and hence prevent carbon deposition thereon which would otherwise be deleterious to the liquid fuel and gaseous nozzles.

Abstract: A cross-fire tube for connecting adjacent combustors in a gas turbine includes a hollow tubular body having couplings at opposite free ends thereof, the hollow tubular body having a substantially circular cross-sectional shape with a maximum diameter region about mid-way between the couplings, tapering in opposite directions to smaller diameters at the free ends. A plurality of purge holes are located in the maximum diameter region.

Abstract: The dual-fuel nozzle includes a liquid fuel nozzle surrounded by an air/gas premixing cup. The cup has a base comprised of swirler vanes surrounding the outer tube of the liquid fuel nozzle. The tip of the liquid fuel nozzle extends to adjacent the open end of the premixing cup opposite the swirler vanes. The interior surface and outer surface of the premix cup and the tip of the liquid fuel nozzle, respectively, at the outer end of the cup are contoured, i.e., tapered complementarily inwardly to avoid recirculation of air in the annulus between the liquid fuel nozzle and the cup. Air recirculation is also prevented, thereby inhibiting flame holding adjacent the base of the cup by providing a smooth transition for air flow through the openings of the swirler at the base of the cup and into the annulus.

Abstract: A liquid fuel injector nozzle for a gas turbine combustor delivers liquid fuel to the combustion chamber in discrete jets. The liquid fuel injector nozzle includes a fuel passage that terminates with a swirl pilot including a plurality of swirl slots for imparting swirl to the liquid fuel. The spin chamber disposed downstream of the swirl pilot is configured to deliver the liquid fuel to the discharge orifice in discrete jets. The discrete fuel streams are concentrated in a fashion to minimize atomization until the fuel adequately penetrates the premixer air stream, resulting in burning properties that lead to increased efficiency, lower emissions, greater flame stability and improved pattern factor when compared to hollow cone spray pattern injection techniques.