Abstract: The claimed invention relates to a method for determining the extent of an oxidation reaction of a coated metallic turbine component within a turbine, comprising determining a plurality of reference oxidation rates for a plurality of locations on the turbine component for a plurality of different turbine operating conditions. The invention also relates to selecting an appropriate oxidation rate from a family of reference oxidation rate data and estimating the oxidation of the coated turbine blade or vane.

Abstract: In one embodiment the present invention provides for a diamond like coating on small particles. This comprises small particles 10 in the size range of approximately 1-1000 nm and a diamond like coating on the small particles. The diamond like coating is distributed over approximately 50-100% of the surface of the small particles and the diamond like coating is one micron or less in thickness. These small particles then may be applied to materials such as resins 12 and insulating tapes.

Abstract: A method for locally repairing a coated article having a bondcoat and a topcoat by removing a first portion of the topcoat and a second portion of the bondcoat and adding a new bondcoat and topcoat material such that the new topcoat material overlies the new bondcoat material and a rim of remnant bondcoat material is provided.

Abstract: The present invention comprises an apparatus and method for efficiently venting impurities from a heat recovery steam generator system by concentrating the impurities in a condensing deaerating vent line 40 and then venting a proportionately small amount of steam with a proportionately high concentration of impurities. The condensing deaerating vent line 40 is attached to a low pressure drum 10, and feed water 54 may be added to the upper portion of the condensing deaerating vent line 40 to improve condensation and conserve thermal energy.

Abstract: The present invention provides for a method and apparatus of horizontally stacking a stator core. A central rail structure 34 that runs down approximately the center axis of the stator frame 2, and attached to the central rail structure are adjustable supports 40 that hold the central rail structure within the stator frame. A dolly 36 is positioned on top of the central rail structure 34. The dolly 36 has multiple finger supports 38 disposed on its top and the finger supports match corresponding grooves in stator core laminations 10. Lamination are placed onto the dolly, gaps in the lamination engage the finger supports on the upper inner diameter of the lamination. This allows for the lamination to be horizontally moved into place within the stator frame.

Abstract: A recreational vehicle includes a chassis having a living space, an electrical system for providing electrical power to the living space, an air conditioner for cooling the living space, a heater for heating the living space, and a plurality of appliances within the living space attached to the electrical system. The recreational vehicle also includes an engine for moving the recreational vehicle, a motor generator for supplying power to the recreational vehicle, a connector for connecting the electrical system of the recreational vehicle to an external power source, and a local area network system electrically connected to the air conditioner, the heater, the plurality of appliances, and the motor generator. The local area network manages the power provided to the to the electrical appliances. A display positioned within the living space shows data related to the air conditioner, the heater, the plurality of appliances, the motor generator and the engine.

Abstract: A mold system for producing components of a turbine engine. The mold system may enable a configuration of a turbine engine component to be changed in less time than conventional systems. The mold system may include a mold formed from mold plates wherein at least one of the mold plates has at least one mold cavity configured to receive a ceramic insert and a ceramic insert positioned in the at least one mold cavity and including a core making cavity. The ceramic insert may be formed from a material having high compressive strength, good wear resistance, good corrosion resistance, good thermal conductivity, and high toughness, such as but not limited to, graphite partially or fully converted to silicon carbide, silicon carbide, graphite coated with silicon carbide, and other appropriate materials. The ceramic insert may also be formed with other near net shape processes, such as, reaction bonded metal oxides.

Abstract: A turbine airfoil usable in a turbine engine and having at least one cooling system. The cooling system may be positioned in an outer wall of the turbine airfoil, and the airfoil may include a hot gas receiving cavity positioned in a mid-chord region of the airfoil. The hot gas receiving cavity may have an opening in a tip of the airfoil to enable hot gases to circulate into the hot gas receiving cavity. In at least one embodiment, the cooling system in the outer wall and the hot gas receiving cavity may include a plurality of ribs. Cooling fluids may be passed through the cooling system in the outer wall, and hot combustion gases may be passed into the hot gas receiving cavity to moderate the temperature of the inner portions of the outer wall to reduce the temperature gradient in the outer wall.

Abstract: A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may be positioned in an outer wall of the turbine airfoil and be formed from a multi-chambered, metering orifice. The multi-chambered, metering orifice may include a first diffusor coupled to a fluid supply channel through a first metering orifice. The first diffusor may be configured to form a vortex of cooling fluids. The multi-chambered, metering orifice may include a second diffusor in communication with an outer surface of the airfoil to exhaust cooling fluids from the airfoil. The second diffusor may be in fluid communication with the first diffusor through a second metering orifice. The second diffusor may be configured to reduce the velocity of the cooling fluids and to enable formation of a film cooling layer on the outer surface of the turbine airfoil.

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 green body ceramic matrix composite material (30) is formed using ceramic fibers (32) in an intermediate state disposed in a green body ceramic matrix material (34). The fibers may be in either a dry but unfired (green) condition or in a partially fired condition. Selective control of the degree of pre-firing (pre-shrinkage) of the fibers may be used to control the level of residual stresses within the resulting refractory material resulting from differential shrinkage of the fibers and the matrix material during processing of the composite material.

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 recreational vehicle includes a chassis having a living space, an electrical system for providing electrical power to the living space, an air conditioner for cooling the living space, a heater for heating the living space, and a plurality of appliances within the living space attached to the electrical system. The recreational vehicle also includes an engine for moving the recreational vehicle, a motor generator for supplying power to the recreational vehicle, a connector for connecting the electrical system of the recreational vehicle to an external power source, and a local area network system electrically connected to the air conditioner, the heater, the plurality of appliances, and the motor generator. The local area network manages the power provided to the to the electrical appliances. A display positioned within the living space shows data related to the air conditioner, the heater, the plurality of appliances, the motor generator and the engine.

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: 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 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.