Abstract: A method for fabricating a syngas cooler is provided. The method includes coupling a tube cage within the syngas cooler, and coupling a plurality of platens to the tube cage to facilitate steam production in the syngas cooler. At least a first platen has at least one of a length that is larger than a length of a second platen, a non-linear geometry, and an angular position that is oblique with respect to a wall of the syngas cooler.

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: 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: 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.