Abstract: A vane unit system having a plurality of vane units having at least one airfoil projecting from a base is modified by placing a hole in the base and receiving a pin which extends between adjacent bases of vane units. A series of modified bases form a rigid ring of vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slit in a casing that receives the vane units allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A vane unit system having a plurality of vane units having at least one air foil projecting from a base. The base has a hole which receives a pin which extends between adjacent bases of vane units therein forming a rigid ring of vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slot in a casing that receives the vane units allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A vane unit system having a plurality of vane units having at least one airfoil projecting from a base is modified by placing a hole in the base and receiving a pin which extends between adjacent bases of vane units. A series of modified bases form a ring of rigid vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slot in a casing that receives the vane units allows for the installation of vane units with pins locking to shims or adjacent vanes without the necessity of having to remove the rotor from the casing. Preferably, the pins are coiled straps resiliently engaging at least one but preferably both holes in two adjacent vanes.

Abstract: A vane unit system having a plurality of vane units having at least one airfoil projecting from a base is modified by placing a hole in the base and receiving a pin which extends between adjacent bases of vane units. A series of modified bases form a rigid ring of vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slit in a casing that receives the vane units allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A vane unit system having a plurality of vane units having at least one air foil projecting from a base. The base has a hole which receives a pin which extends between adjacent bases of vane units therein forming a rigid ring of vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slot in a casing that receives the vane units allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A dual-fluid heat engine having a gas turbine and an open cycle steam turbine. The gas turbine has a compressor for compressing a first working fluid, the compressor having a compressor outlet. The gas turbine has a combustion chamber in fluid communication with the compressor outlet. The turbine portion of the gas turbine has an inlet in fluid communication with the combustion chamber for performing work by expansion of the first working fluid, and a gas turbine exhaust. A heat recovery exchanger is coupled to the gas turbine exhaust having a heat recovery inlet and an outlet for heating a second working fluid, water. The water is converted into steam in the heat recovery exchanger. A pump increases the pressure of the water prior to entrance in the heat recovery exchanger. An atmospheric exhaust expansion steam turbine extracts energy from the heated second working fluid to drive an electrical generator.

Abstract: A vane unit system having a plurality of vane units having at least one air foil projecting from a base. The base has a hole which receives a pin which extends between adjacent bases of vane units therein forming a rigid ring of vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slot in a casing that receives the vane units, allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A dual-fluid heat engine having a gas turbine and an open cycle steam turbine. The gas turbine has a compressor for compressing a first working fluid, the compressor having a compressor outlet. The gas turbine has a combustion chamber in fluid communication with the compressor outlet. The turbine portion of the gas turbine has an inlet in fluid communication with the combustion chamber for performing work by expansion of the first working fluid, and a gas turbine exhaust. A heat recovery exchanger is coupled to the gas turbine exhaust having a heat recovery inlet and an outlet for heating a second working fluid, water. The water is converted into steam in the heat recovery exchanger. A pump increases the pressure of the water prior to entrance in the heat recovery exchanger. An atmospheric exhaust expansion steam turbine extracts energy from the heated second working fluid to drive an electrical generator.

Abstract: An inlet air heating system for a gas turbine comprising a main air inlet; ducting leading from the main inlet to an inlet of the gas turbine; a manifold located adjacent the inlet for feeding intermediate temperature air into the ducting; a conduit connected to the inlet air manifold, the conduit having an ambient air inlet and connected to a compressor bleed air conduit, downstream of the ambient air inlet; and one or more eductors in the conduit through which the bleed air flows to entrain the ambient air into the conduit through the ambient air inlet and to mix the bleed air and ambient air for introduction into the ducting through the manifold.

Abstract: Turbine buckets are designed for use in an environment of ultra-high temperatures by incorporating therein water cooling channels using preformed tubes which are located beneath an outer protective layer. This layer is preferrably composed of an inner skin which provides high thermal conductivity and an outer skin which provides protection from hot corrosion.

Abstract: An arrangement is provided for supplying liquid coolant to liquid-cooled turbine buckets of a gas turbine power plant. The buckets have internal coolant passages and the outer rims of turbine discs have coolant channels which communicate coolant from the discs to the passages in the buckets. The forward, intermediate and aft discs with sealing spacers interposed between adjacent discs are mounted on a shaft. The arrangement includes a forward flange, an intermediate flange and an aft flange. The flanges are adjacent to the corresponding discs. The forward and aft flanges, the discs and the spacers have a plurality of aligned axially extending apertures circumferentially disposed about the shaft. Bolts extend through the apertures to secure the discs, spacers and flanges in abutting contact. Each of the interposed spacers cooperates with a corresponding disc to form a circumferentially disposed chamber.

Abstract: Turbine buckets are designed for use in an environment of ultra-high temperatures by incorporating therein water cooling channels using preformed tubes which are located beneath an outer protective layer. This layer is preferably composed of an inner skin which provides high thermal conductivity and an outer skin which provides protection from hot corrosion.