Abstract: A secondary fuel delivery system for delivering a secondary stream of fuel and/or diluent to a secondary combustion zone located in the transition piece of a combustion engine, downstream of the engine primary combustion region is disclosed. The system includes a manifold formed integral to, and surrounding a portion of, the transition piece, a manifold inlet port, and a collection of injection nozzles. A flowsleeve augments fuel/diluent flow velocity and improves the system cooling effectiveness. Passive cooling elements, including effusion cooling holes located within the transition boundary and thermal-stress-dissipating gaps that resist thermal stress accumulation, provide supplemental heat dissipation in key areas.

Abstract: A method of connecting a superconducting fault current limiter to an alternating current generator to limit a current flowing in the generator is disclosed. A superconducting fault current limiter is connected in proximity with the generator to limit the current flowing in the generator. A system comprising a superconducting fault current limiter, a generator and a circuit is also disclosed.

Abstract: A gas turbine engine is provided comprising an outer shell, a compressor assembly, at least one combustor assembly, a turbine assembly and duct structure. The outer shell includes a compressor section, a combustor section, an intermediate section and a turbine section. The intermediate section includes at least one first opening and at least one second opening. The compressor assembly is located in the compressor section to define with the compressor section a compressor apparatus to compress air. The at least one combustor assembly is coupled to the combustor section to define with the combustor section a combustor apparatus. The turbine assembly is located in the turbine section to define with the turbine section a turbine apparatus.

Abstract: A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane.

Abstract: A combustion catalyst coating (36) applied to the surface of a ceramic thermal barrier coating (34) which is supported by a metal substrate (32). The microstructure of the thermal barrier coating surface provides the necessary turbulent flow and surface area for interaction of the catalyst and a fuel-air mixture in a catalytic combustor of a gas turbine engine. The temperature gradient developed across the thermal barrier coating protects the underlying metal substrate from a high temperature combustion process occurring at the catalyst surface. The thermal barrier coating deposition process may be controlled to form a microstructure having at least one feature suitable to interdict a flow of fuel-air mixture and cause the flow to become more turbulent than if such feature did not exist.

Abstract: Disclosed are novel nickel-base alloy compositions that may be cast as a single crystal or directionally solidified alloy consisting essentially of, by weight: 8-12% Cr, 10-14% Co, 0.3-0.9% Mo, 3-7% W, 2-8% Ta, 2.0-5.5% Al, 1.5-5.0% Ti, up to 2% Nb, less than 0.1% B, less than 0.1% Zr, 0.05-0.15% C, less than 0.5% Hf, 2-4% Re, 0.05-0.2% Si, up to 0.015% S, up to 0.1% La, up to 0.1% Y, up to 0.1% Ce, up to 0.1% Nd, up to 0.1% Dy, up to 0.1% Pr, up to 0.1% Gd, balance is Ni, and wherein (La+Y+Ce+Nd+Dy+Pr+Gd) is 0.001-0.1%. The compositions for the nickel-base superalloy have a balance between oxidation resistance, corrosion resistance, castability, and mechanical properties, such as creep resistance and thermo-mechanical fatigue resistance.

Abstract: A centerline suspension arrangement (42) for a turbine (40). A turbine inner casing (44) is supported within an outer casing (46) via a support member (60) that includes an inner portion (62) contacting the inner casing and an outer portion (66) extending into a slot (68) formed in the outer casing. The support member is slid into an axially oriented slot (64) formed in the inner casing and is body bound therein with respect to radial movements, with the support member and the inner casing slot including opposed vertical support surfaces (82, 90) and a pair of oppositely facing opposed horizontal support surfaces (80, 88 and 86, 92). Thus, dead weight and operating loads from the inner casing are reacted through the support member and into the outer casing without the necessity for any bolting or other fastener attachment in the design load path between the support member and the inner casing.

Abstract: The present invention comprises a method and apparatus for installing a stator core, or portions thereof, into a power generator frame 2 that comprises assembling the stator core inside of a container 60, and then moving the container to the power generator 1. The container 60 is horizontally aligned with the power generator 1, and the stator core is transferred from the container to the power generator.

Abstract: A multi-stage selective catalytic reduction (SCR) unit (32) provides efficient reduction of NOx and other pollutants from about 50-550° C. in a power plant (19). Hydrogen (24) and ammonia (29) are variably supplied to the SCR unit depending on temperature. An upstream portion (34) of the SCR unit catalyzes NOx+NH3 reactions above about 200° C. A downstream portion (36) catalyzes NOx+H2 reactions below about 260° C., and catalyzes oxidation of NH3, CO, and VOCs with oxygen in the exhaust above about 200° C., efficiently removing NOx and other pollutants over a range of conditions with low slippage of NH3. An ammonia synthesis unit (28) may be connected to the SCR unit to provide NH3 as needed, avoiding transport and storage of ammonia or urea at the site. A carbonaceous gasification plant (18) on site may supply hydrogen and nitrogen to the ammonia synthesis unit, and hydrogen to the SCR unit.

Abstract: A stator coil includes a plurality of copper strands and a layer of high thermal conductivity polymer disposed adjacent at least one of the copper strands. The high thermal conductivity polymer includes a host polymer and a high thermal conductivity filler. The high thermal conductivity polymer improves heat transfer from the plurality copper strands.

Abstract: Polymer brushes (50) in a resin that create phonon pathways therein The polymer brushes themselves comprise structured polymer hairs having a density of 0.8 to 1.0 g/cc, a chain length of 1 to 1000 nm, and a thermal conductivity of 0.5 to 5.0 W/mK. The polymer brushes are 10-25% by volume of the resin, and the polymer hairs can orient surrounding resin molecules to the polymer hairs alignment (55).

Abstract: Aspects of the invention relate to a system and method for actively controlling compressor clearances in a turbine engine by passing a thermal fluid in heat exchanging relation through a compressor vane carrier. During some operational conditions, such as hot restart or spin cool, it may be desirable to heat the vane carrier to enlarge or at least prevent a decrease in compressor clearances. In such cases, a heated thermal fluid can be provided by reclaiming residual exhaust energy from a heat recovery steam generator. At any condition where improved performance is desired, such as at base load operation, the vane carrier can be cooled to minimize compressor clearances. A cooled thermal fluid can be bleed air from an upstream portion of the compressor, water-cooled high pressure bleed air from a downstream portion of the compressor, or feed water from the bottoming cycle in a combined cycle engine.

Abstract: A means (22) for structurally stiffening or reinforcing a ceramic matrix composite (CMC) gas turbine component, such as an airfoil-shaped component, is provided. This structural stiffening or reinforcing of the airfoil allows for reducing bending stress that may be produced from internal or external pressurization of the airfoil without incurring any substantial thermal stress. The stiffener is disposed on a CMC wall and generally extends along a chord length of the airfoil.

Abstract: A cooling system for a turbine blade of a turbine engine having multiple serpentine trailing edge cooling channels in parallel. The serpentine cooling channels are positioned proximate to a trailing edge of the turbine blade and facilitate increased heat removal with less cooling fluid flow, thereby resulting in increased cooling system efficiency.

Abstract: A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from fore and aft end supports and a locking device having fore and aft angled surfaces for urging the fore and aft end supports into lateral recesses in the disc groove. The locking spacer assembly may also include a mid spacer positioned between the fore and aft end supports. A retainer may be attached to the locking device to draw the fore and aft angled surfaces of the locking device into contact with the fore and aft support surfaces and urge the first and second end supports into lateral recesses in the disc groove.

Abstract: A method of using a Graphic User Interface (GUI) for interactive virtual inspection of modeled objects. The method includes acquiring a three-dimensional model of a modeled object and displaying a first view of the modeled object for a user to identify locations of interest on a surface of the modeled object visible within the first view. The user enters information to create a markup tag that annotates the location of interest, and the markup tag is automatically associated with the location of interest on the modeled object. A second view of the modeled object is displayed including the user identified location of interest and the markup tag.

Abstract: A method of coalescing information about inspected objects. The method includes acquiring an image set of an object to be inspected, the image set having a three-dimensional model of the object and a plurality of two-dimensional images of the object. A location of interest is identified on a surface of the modeled object and global coordinate points of the three-dimensional model are designated that characterize the location of interest of the modeled object. A markup tag annotating the location of interest is associate with the designated global coordinate points of the three-dimensional model, and the markup tag is conveyed when viewing any one of the plurality of two-dimensional images of the image set that have at least one image point that correlates to a corresponding designated global coordinate point of the three-dimensional model that characterize the location of interest.

Abstract: A seal assembly is provided to prevent leakage of cooling fluid from a generator housing. A bracket 26 includes an inlet connectable to power plant piping for receiving a supply of sealing fluid. The inlet is in communication with a bracket passageway 32 for admitting the sealing fluid in a radially inner section of the bracket. A sealing cartridge 28 is mountable in an annulus defined by the bracket. The sealing cartridge includes at least one cartridge passageway 44 in communication with the bracket passageway for admitting the supply of sealing fluid and passing the supply of sealing fluid to establish a sealing boundary about the rotor shaft. At least one of the bracket or the sealing cartridge includes a first sealing fluid-distribution channel 30 extending along a radial direction for providing fluid communication between the bracket passageway and the at least one passageway in the sealing cartridge.

Abstract: A method of stress relief for stainless steel combustion turbine components includes vibrating the components during welding at a subharmonic frequency. The proper frequency is selected to be below a harmonic frequency, and to produce an amplitude in the range of ¼ to ½ the amplitude produced by a harmonic frequency. The component to be repaired is vibrated during and after welding at this frequency.

Abstract: A combustion turbine power plant (10) incorporating a desiccating scrubber (140) for simultaneously removing water and sulfur from a flue gas (20) of the power plant (10). The desiccating scrubber (140) may include an inlet nozzle (145) for spraying an aqueous solution (142) containing a desiccant and a base into flue gas (20) so the aqueous solution (142) makes direct contact with flue gas (20). A filter (162) may be provided to collect sulfur compounds downstream of the desiccating scrubber (140) and a regenerator (164) may be provided for recovering water. A controller (148) may control a base supply (170) and a desiccant supply (172) to regulate the respective amounts of each introduced into the aqueous solution (142). Controller (148) may be responsive to sensors (142) measuring the water and sulfur content of flue gas (20) exhausted to atmosphere (144). The desiccating scrubber (140) may include a demister (160) to entrain carryover droplets from a sprayed aqueous solution (142).