Abstract: A gas turbine cycle that utilizes the vaporization of liquefied natural gas as a source of inlet air chilling for a gas turbine. The cycle uses regeneration for preheating of combustor air and offers the potential of gas turbine cycle efficiencies in excess of 60%. The systems and methods permit the vaporization of LNG using ambient air, with the resulting super cooled air being easier to compress and/or having fewer contaminants therein. As the air is easier to compress, less energy is needed to operate the compressor, thereby increasing the efficiency of the system. A portion of the vaporized natural gas may be used as the combustion fuel for the gas turbine system, thereby permitting multiple turbines to be operated using a single topping cycle. In alternative embodiments, the vaporization of the LNG may be used as part of a bottoming cycle to increase the efficiencies of the gas turbine system.

Abstract: A turbine airfoil usable in a turbine engine and having at least one cooling system. The cooling system may include a pressure side serpentine cooling channel and a suction side serpentine cooling channel. The cooling channels may be nested within each other to optimize heat exchange between the cooling fluids and the materials forming the airfoil, to reduce the amount of cooling fluids required, to reduce the required pressure of the cooling fluids, and to provide other benefits. The pressure side serpentine cooling channel may pass cooling fluids chordwise towards the trailing edge, and the suction side serpentine cooling channel may pass cooling fluids chordwise towards the leading edge.

Abstract: Methodologies for non-destructively inspecting and characterizing micro-structural features in a thermal barrier coating (TBC) on a component, wherein the micro-structural features define pores and cracks, if any, in the TBC. The micro-structural features having characteristics at least in part based on a type of process used for developing the TBC and affected by operational thermal loads to which a TBC is exposed. In one embodiment, the method allows detecting micro-structural features in a TBC, wherein the detecting of the micro-structural features is based on energy transmitted through the TBC, such as may be performed with a micro-feature detection system 20. The transmitted energy is processed to generate data representative of the micro-structural features, such as may be generated by a controller 26. The data representative of the micro-structural features is processed (e.g.

Abstract: An imaging system (110) for imaging a scene with a detector array (104) having an array of imaging elements is provided. The imaging system (110) includes an image estimation module (202) for generating a plurality estimates of uncorrupted images based upon a plurality of noisy images generated by the detector array (104). The imaging system (110) further includes a parameter determination module (204) for determining one or more nonuniformity correction parameters based upon the estimates of uncorrupted images.

Abstract: An article comprising a ceramic material having a ceramic matrix composite backing adapted for use in a gas turbine engine is provided. The article comprises a structural ceramic material having a hot side facing toward a high temperature environment and a cold side facing away from the high temperature environment; and a ceramic matrix composite composition having a strength greater than the strength of the ceramic material attached to the back of the cold side of the ceramic material, whereby crack initiation and propagation are inhibited by the ceramic matrix composition to a greater degree than by the ceramic material.

Abstract: A turbine vane usable in a turbine engine and having at least one cooling system. The cooling system may include at least one convergent flow channel for receiving air from a shroud assembly. The cooling system may also include impingement channels in a leading edge cavity for impinging a cooling fluid against an inner surface of a leading edge of the turbine vane. The cooling system may also include a serpentine cooling path for removing heat from aft sections of the turbine vane proximate to the trailing edge of the turbine vane. The cooling system may also include a divergent leading edge cavity. Exterior film cooling is not needed to safely operate a turbine vane according to this invention.

Abstract: A business management method with interaction between an electrical energy supplier and a plurality of customer energy consumers includes the consumers providing respective electricity load profiles to the energy supplier. The method also includes the energy supplier aggregating the respective projected electricity load profiles. The method further includes the energy supplier making decisions based on the respective projected electricity load profiles on any of the consumers bidding on additional power, offering excess power on energy exchanges, and offering specials discounts to favored consumers. The method is likewise applicable to other commodities such as a water supply, fuel gas supply, or the like.

Abstract: A catalytic combustor for a combustion turbine that employs a protective nickel aluminide diffusion barrier on its inside and outside surfaces with a porous alumina, zirconia, titania, and/or ceria, and bond phase coating on the outside surface in which a catalyst is contained.

Abstract: A heat shield for a transition of a turbine engine for coupling a transition component of a turbine engine to a turbine vane assembly to direct combustor exhaust gases from the transition into the turbine vane assembly. The heat shield may be capable of reducing the temperature differential across a transition bracket extending from a transition component, thereby reducing the likelihood of premature failure of the bracket or the transition, or both. The heat shield may reduce the temperature differential by insulating the transition bracket and transition bracket rib from cooling gases. The heat shield may be formed from a tubular elongated body having first and second end attachments configured to attach the elongated heat shield body to the transition.

Abstract: Aspects of the invention are directed to systems for reducing the cooling requirements of a ring seal in a turbine engine. In one embodiment, the ring seal can be made of a ceramic material, such as a ceramic matrix composite. The ceramic ring seal can be connected to metal isolation rings by a plurality of pins. The hot gas face of the ring seal can be coated with a thermal insulating material. In another embodiment, the ring seal can be made of metal, but it can be operatively associated with a ceramic heat shield. The metal ring seal can carry the mechanical loads imposed during engine operation, and the heat shield can carry the thermal loads. By minimizing the amount of ring seal cooling, the ring seal systems according to aspects of the invention can result in improved engine performance and emissions.

Abstract: A blade assembly (10) for a turbine (16) including a vibration damper (12) having a mounting base (38) sealingly disposed at an inlet end (24) of a cooling fluid passageway (22) within the root section (20) of the blade assembly and including an opening (40) in the mounting base for passing cooling fluid into the cooling passageway. The opening is sized to function effectively as an orifice for limiting a maximum flow rate of cooling fluid in the event of a breach of the cooling fluid passageway downstream of the inlet end. A wear feature (34) is formed on the distal end of the vibration damper opposed the mounting base for rubbing interface with a complementary wear feature attached to a wall (26) of the cooling fluid passageway. The wear feature may include a non-planar wear surface such as angularly disposed wear surfaces (58, 60) effective to resist vibrational movement in two directions.

Abstract: Aspects of the invention relate to a system for monitoring the wear of a component. A conductor can be embedded in the component at a depth from a surface of the component. In one embodiment, the conductor can be operatively connected to a power source to form an electrical circuit. The resistance across the conductor can be measured. As the component contacts a second component, the component can begin to wear. Once the wear progresses to the conductor, changes in the measured resistance can result. Thus, an operator can be alerted that the component has worn to a certain point and that service may be needed. Alternatively, impedance can be measured across the conductor. Because the dielectric permeability of the material surrounding the conductor can affect impedance, changes in impedance can occur as the surface material of the component is worn away.

Abstract: A cooling system for a turbine airfoil of a turbine engine having multiple segmented ribs aligned together spanwise within a trailing edge cooling channel. The segmented ribs may be positioned proximate to a trailing edge of the turbine airfoil to facilitate increased heat removal with less cooling fluid flow, thereby resulting in increased cooling system efficiency, and to increase the structural integrity of the trailing edge of the airfoil. The segmented ribs may include crossover orifices that provide structural integrity to ceramic cores used during manufacturing to prevent cracking and other damage.

Abstract: A method of controlling a gas turbine system (10) may include controlling an inlet guide vane position (98) to maintain a turbine (24) exhaust temperature at a corrected value that is a function of a compressor (12) inlet temperature and a turbine (24) normalized load. The method may include selecting the minimum value (138) of a part load tunable value, a part load maximum value and a fixed maximum value of a turbine (24) exhaust temperature for the corrected value. A corrected value setpoint may be determined (94) for the gas turbine system (10) operating at a part load condition where at least one of a fuel flow rate and the inlet guide vane position is controlled (98) so the corrected value does not exceed the corrected value setpoint. The corrected value may prevent a turbine (24) engine from exceeding its firing temperature during operation and ensure the engine operates within combustor dynamics and emissions limits.

Abstract: An electrically insulated object 13 with a heat conduit at the interface between the layers of insulating tape 16. The tape 16 has been, surface coated with a high thermal conductivity (HTC) material, so that the interface between the layers of tape 23 provides a pathway for the heat to reach the environment 24. The radiation of heat through the tape layers is also increased by the surface coatings.

Abstract: The present invention relates to homogeneous alumoxane-LCT-epoxy polymers and methods for making the same. The homogeneous alumoxane-LCT-epoxy polymers comprise alumoxane-containing sub-structures evenly dispersed and essentially completely co-reacted with the LCT-epoxy sub-structures. The alumoxane sub-structures are organically bonded to the LCT-epoxy sub-structures. This produces homogeneous alumoxane-LCT-epoxy polymers that are substantially free of particle wetting and micro-void formation, with improved thermal conductivity properties without compromising on other desired structural integrities.

Abstract: An airfoil (44) formed of a plurality of pre-fired structural CMC panels (46, 48, 50, 52). Each panel is formed to have an open shape having opposed ends (54) that are free to move during the drying, curing and/or firing of the CMC material in order to minimize interlaminar stresses caused by anisotropic sintering shrinkage. The panels are at least partially pre-shrunk prior to being joined together to form the desired structure, such as an airfoil (42) for a gas turbine engine. The panels may be joined together using a backing member (30), using flanged ends (54) and a clamp (56), and/or with a bond material (36), for example.

Abstract: A measurement device for measuring the wear of turbo-machine components to reduce the likelihood of component failure while a turbine-machine is at load. The measurement device is capable of measuring and calculating a distance between surfaces while the turbo-machine is at load. The distance may be compared with a measurement taken of the same location at another time to determine wear of a surface remote from the location of the measurement. The measurement device may be configured such that multiple measurements may be made on a single turbine engine by moving the measurement device from location to location.

Abstract: A turbine vane usable in a turbine engine and having at least one cooling system. The cooling system includes three diffusors in an outer wall of the vane for reducing the velocity of the cooling fluids exiting the turbine vane. One of the diffusors is formed from one or more cavities in an outer wall of the turbine vane for heat dissipation. The cavities may be supplied with cooling fluids from an internal cooling cavity through one or more interior metering orifices. The cooling fluids may exit the cooling cavity through one or more exterior metering orifices, which are second diffusors, and diffusion slots, which are third diffusors, that reduce the velocity of the cooling fluids and enable formation of a film cooling layer on the outer surface of the turbine vane.

Abstract: A turbine fuel ring assembly includes a fuel distribution ring, at least one fuel supply tube attached to the fuel distribution ring and at least one attachment leg connected to the fuel distribution ring. The fuel ring has a hollow interior and a plurality of apertures for expelling a fluid. The attachment leg is configured to allow flexibility due to thermal expansion induced under certain load conditions such as during engine start-up or shut-down. Further, the configuration of the attachment legs provides improved stress distribution characteristics. The fuel supply tube includes a rectangular passage and a round passage that are disposed substantially transverse to each other and in fluid communication with each other and with the hollow interior of the fuel distribution ring. The rectangular passage and the round passage have substantially identical cross-sectional areas. The fuel supply tube is configured to avoid structural interferences with neighboring components.