Abstract: A combustor in which fuel is introduced into a combustion zone at a first acute angle with respect to the radially outward direction so as to swirl the fuel about the combustor axis, thereby improving the stability of the combustion process. Combustion air is introduced into the combustion zone at a second acute angle with respect to the radially inward direction so as to swirl the air about the combustor axis in the same circumferential direction that the fuel is swirled, with the first and second acute angles being approximately equal. By swirling the combustion air in a manner that is compatible with the swirling of the fuel, noise associated with the combustion process is reduced.

Abstract: A coal fired gas turbine system with an integral topping combustor is provided for generating rotating shaft power by consuming coal. A carbonizer converts coal to a char and a gas fuel. The char is burned in a pressurized fluidized bed combustor (PFBC) supplied with compressed air from a gas turbine. The hot gas from the PFBC is directed to a topping combustor for further heating by burning the gas fuel produced by the carbonizer. The topping combustor is comprised of a plurality of cylindrical combustor cans disposed within a cavity formed by the gas turbine casing between the compressor and turbine sections. A perforated baffle disposed in the cavity creates a plenum so that the hot gas entering the casing through four pipes arranged about its periphery is uniformly distributed among the combustor cans.

Abstract: A compressor diaphragm assembly for combustion turbines includes a plurality of vane airfoils, each of which is formed with an integral inner shroud and an integral outer shroud, joined together by connecting bars which transfer loads between the vane airfoils and the casing slots of the turbine within which the vane airfoils are suspended.

Abstract: A compressor diaphragm assembly for combustion turbines includes a plurality of vane airfoils, each of which is formed with an integral inner shroud. A segmented seal carrier is suspended from the inner shrouds, and an outer ring supports the plurality of vane airfoils from a casing portion of the turbine in a parallel relationship at a predetermined angle with respect to the longitudinal axis of the turbine. The outer ring has one or more grooves formed at the predetermined angle to engagably receive respective rows of the vane airfoils at their outer portion. Each seal carrier segment includes a pair of disc-engaging seals, and is formed to be engaged with the inner shrouds of one or more vane airfoils, in order to provide a labyrinth seal with discs assembled to form a rotating shaft.

Abstract: A fuel nozzle assembly having a cylindrical nozzle tip at one end of a fuel delivery tube and a supporting flange at the other end. An air delivery tube, also secured to said support flange, encloses the fuel delivery tube to define an annular air chamber therebetween. A cylindrical face of the nozzle tip is received in an similarly sized and shaped opening in a swirl cap attached to the end of the fuel delivery tube to slideably engage the air delivery tube and the fuel delivery tube and to define a substantially constant radial spaced relationship between the cylindrical nozzle tip and the air delivery tube during variable axial expansion of the fuel delivery tube and air delivery tube. The air delivery tube is secured to the fuel delivery tube by mounting a radially expansive portion of the air delivery tube to the support flange.

Abstract: The invention comprises sealing structure between a seal plate, a rotor, and a blade, for sealing the root portion of a rotor and blade assembly to provide a sealed chamber adjacent the base of the root into which radially directed passageways in the blade open for transmitting the cooling fluid, delivered to the chamber, through the blade to the tip end thereof to cool the blade. The seal is perfected through a wedging action caused by centrifugal force moving the base or foot of the plate, disposed below the blade root, into sealing engagement with the rotor disk, and an intermediately disposed seal bar extending arcuately just radially outwardly of the radially innermost portion of the root and generally in the vicinity of the innermost loaded root projection with the loaded root providing the axial seal and the sealing bar and seal plate foot providing the radial seals to define a cooling fluid chamber adjacent the base of the root.