Abstract: Embodiments of the invention relate to a robust turbine vane made of stacked airfoil-shaped CMC laminates. Each laminate has an in-plane direction and a through thickness direction substantially normal to the in-plane direction. The laminates have anisotropic strength characteristics in which the in-plane tensile strength is substantially greater than the through thickness tensile strength. Thus, the laminates can provide strength in the direction of high thermal gradients and, thus, withstand the associated high thermal stresses. The laminates are relatively weak in through thickness (interlaminar) tension, but, in operation, relatively low through thickness tensile stresses can be expected. The laminates can be strong in through thickness compression; accordingly, the laminate stack can be held in through thickness compression by one or more fasteners.

Abstract: A leak detector for mixed heat exchangers. In mixed heat exchangers it is important to monitor leaks from the liquid flows to the gas flows since liquid can damage delicate machinery. A barrier is mounted on the gas side of the heat exchanger. The barrier contains at least two thermometers, one of which is thermally isolated from the gas flow inside of the barrier, and another which is in contact with the barrier. When cooler water droplets and vapor enter the gas flow they will come into contact with the barrier. This will lower the measured temperature dramatically in the thermometer which is in contact with the barrier, while the isolated thermometer will not have its measured temperature quickly lowered by the leak. Therefore a different in the measurement in the change in temperature of the thermometers will indicate a leak in the heat exchanger.

Abstract: A method of repairing a combustion turbine component having damage located at or near a cooling hole or hollow or geometrically complex portion of the component is provided. The method comprises forming a preparatory groove that extends from a surface of the component to the damaged area but does not extend to the cooling hole or hollow or geometrically complex portion of the component, the groove extending 40–90% the distance from the component to the damaged area; spraying a filler material into the groove with a micro-plasma torch at a current of less than 50 amperes; and filling the groove with the filler material such that the heated filler material substantially extends from the cooling hole or hollow or geometrically complex portion of the component to a surface of the component.

Abstract: According to a method for producing a solid ceramic fuel cell, a solid electrolyte layer is gas-tightly deposited on an electrode inside a coating chamber, using a plasma spraying technique. The pressure inside the coating chamber is set at less than approximately 15 mbar for this purpose. A coating material is powder form, preferably with a particle diameter of significantly less than 10 ?m, is finely dispersed in the plasma jet in such a way that the individual particles are isolated from each other when they meet the electrode. This enables a very homogenous and impervious solid electrolyte layer to be deposited.

Abstract: A gas turbine airfoil (34) includes sequentially connected, radially displaced chambers (e.g., 46, 58) within the airfoil. A cooling fluid supply chamber (46) is disposed within a first section (48) of a leading edge portion (36) of the airfoil and receives a cooling fluid flow (50). The cooling fluid supply chamber is in fluid communication with a first leading edge impingement chamber (52) disposed against a backside (44) of the leading edge portion. A discharge chamber (58) in serial fluid communication with the first impingement chamber is disposed radially outward of the first impingement chamber and within a second section (60) of the leading edge portion. A second leading edge impingement chamber (62) in fluid communication with the discharge chamber is disposed against a backside (64) of the leading edge portion in the second section. The chambers may be arranged to limit centrifugal force-induced pressure buildup in the respective chambers.

Abstract: A turbine blade for a turbine engine having a cooling system with at least one serpentine cooling channel in internal aspects of the turbine blade. The serpentine cooling channel includes at least one root turn proximate to a root of the turbine blade. The root turn may have a generally rectangular shape and may account for reduced pressure losses relative to conventional curved root turns. One or more refresh holes may be positioned in a rib proximate to the root turn to provide the root turn with cooling fluids that have bypassed the first and second legs of the serpentine cooling channel.

Abstract: A composite turbine disc includes a bore section providing a first set of mechanical and temperature resistance properties, and a rim section which provides a second set of mechanical and temperature resistance properties. The second set of mechanical properties and temperature resistance are superior to the first set of properties. An intermediate diaphragm section is disposed between the bore section and the rim section. The intermediate section has mechanical and temperature resistance properties in a range between the first and second set of properties.

Abstract: A non-stick material coated glass slip layer for use in insulating tapes for electrical conductors. A conductive glass tape is interwoven with a non-stick material coated glass tape to form the slip layer. The slip layer is sandwiched between and inner conductive layer that is in contact with and electrical conductor, and an cater conductive layer that is in contact with machinery, such as a generator. The slip layer allows for a difference of movement between the inner conductive layer and the outer conductive layer without damage to the insulating tape.

Abstract: A turbine blade for a turbine engine having an internal cooling system formed from a plurality of cooling chambers extending radially in the blade and configured to create vortices within the chambers. In at least one embodiment, the cooling system may be formed from leading edge cooling chambers, trailing edge cooling chambers, suction side mid-chord cooling chambers, and pressure side mid-chord cooling chambers that are configured to receive cooling fluids from supply channels in a root of the blade and to create vortices in the cooling chambers. The vortices of cooling fluids increase heat removal from the turbine blade. The cooling fluids may be exhausted from the turbine blade through film cooling orifices.

Abstract: An interconnecting assembly for a rotor assembly of a dynamoelectric machine is provided. The interconnecting assembly may be part of a conductive path generally extending from a radially inward section of the rotor assembly to a winding located at a radially outward section of the rotor assembly. The interconnecting assembly may be made up of a flexible member (44) comprising a bend (50). The interconnecting assembly may be further made up of a connector (70) connected to the flexible member to pass axial and radial forces that develop during operation of the machine. The positioning of the connector relative to the flexible member may be arranged so that an effect of an axial force on a radius of curvature of the bend and an effect of a radial force on that radius of curvature are opposed to one another. This leads to lower peaks of mechanical stress at the flexible member (44) (e.g.

Abstract: A gas turbine includes a compressor, a combustor, a turbine, and a flow path diverting an excess portion of the compressed air produced by the compressor around the turbine. The flow path conducts the excess portion into a turbine exhaust gas flow producing a cooled exhaust gas. A method of operating the gas turbine includes opening an inlet guide vane of the compressor to allow the compressor to produce an increased volume of compressed air. The increased volume exceeds a volume of compressed air needed to support combustion. An excess portion of the compressed air is directed into the exhaust gas to produce a cooled exhaust. In a combined cycle power plant, the cooled exhaust from the gas turbine may be used to warm a steam turbine portion to a desired temperature while allowing operation of the gas turbine at a power level that produces exhaust gas at a temperature higher than the desired temperature.

Abstract: A business management method for remote detection of anomalies with interaction between an electric distribution company and a plurality of customer energy consumers with respective electric metering systems, comprises the steps of: the consumers providing respective metering system data to the electric distribution company; the electric distribution company monitoring the respective electric metering system data; the electric distribution company monitoring for anomalies in the data; the electric distribution company performing remote online diagnostics upon detection of an anomaly; upon a finding that the electric metering system of a respective customer energy consumer is functioning properly, the electric distribution company notifies the respective customer energy consumer; and upon a finding that the electric metering system of a respective customer energy consumer is not functioning properly, the electric distribution company schedules a repair visit with the respective customer energy consumer.

Abstract: Aspects of the invention relate to a system for assessing the condition of a thermal barrier coating on a turbine vane during engine operation. According to embodiments of the invention, one or more wires can be passed along the airfoil portion of the vane. The wires can extend over, within, or beneath the thermal coating. An electrical current can be passed along the wires, and electrical resistance can be measured across the wires. Thus, if a portion of the thermal coating becomes damaged, then the wires located in that area may break. A disconnect in the wires can lead to an increase in resistance across the wires, which can alert an operator to a problem. Some assessment systems can provide a general indication of the magnitude of damage and whether the damage is spreading.

Abstract: An improved generator rotor (30) and a method of repairing an existing generator rotor (12) are disclosed. Methods consistent with the present invention provide techniques for repairing existing stress-damaged rotors (12) to remove stress-induced cracks (29), without requiring new retaining rings (16), to significantly extend the useful life of a generator without the cost and complexity of conventional repair techniques. Improved generator rotors (30) consistent with the present invention provide a tooth-top design that is more resistant to stress-induced cracking than conventional designs, resulting in new generators with longer useful lives.

Abstract: A device, system, and method for securing a turbine engine seal in a retracted position enabling maintenance, assembly and disassembly of the turbine engine. The system can include a retainer arranged to retain the seal in a retracted position and constructed to fail at an engine operating temperature. Failure of the retainer allows movement of the seal from the retracted position to an operational position.

Abstract: An inspection system includes a cooling apparatus for conducting visual inspections within operating temperature environments, such as, for example, the interior of a combustion turbine shortly after shut down. The cooling apparatus provides cooling for an inspection probe such as a video borescope. The cooling apparatus includes an articulating guide tube having a control portion, an elongate flexible portion and an articulating section. The video borescope is inserted down through the articulating guide tube. A thermal protective sleeve surrounds and thermally insulates a portion of the articulating guide tube. Vortex coolers circulate cooled, compressed air within the cooling apparatus, thereby maintaining a cool video borescope operating temperature.

Abstract: A weld preparation process that translates a consumable or nonconsumable tool over an area that is subsequently to be welded to impart friction heating to the surface. Rotary or linearly oscillated motion between the tool and the workpiece is used to generate heat and produce deformation in the surface, resulting in recrystallization of the area being processed and a compressive residual stress.

Abstract: A tooling for affecting the repair of turbine blade tips which generates bond line loads as a result of differential thermal expansion between the work piece and the fixture. The fixture accommodates multiple work pieces of different sizes to facilitate a batch repair process and compressive load limits are established by insertion of deformable compression rings.

Abstract: A gas turbine airfoil (e.g. 12) includes a pressure sidewall (14) and a suction sidewall (16) joined along respective leading and trailing edges (18, 20) and extending radially outward from an inner diameter (26) to an outer diameter (22). The airfoil includes a plurality of suction side flow channels (52) extending chordwise within the suction sidewall and having respective heights selected to achieve a desired degree of cooling for the suction sidewall. The airfoil also includes a plurality of pressure side flow channels (30) extending chordwise within the pressure sidewall and having respective heights selected to achieve a desired degree of cooling for the pressure sidewall. A transition region (58) is provided in each flow channel wherein the height of the channel is reduced to an outlet height so that respective outlets of the flow channels can each be independently disposed in the trailing edge.

Abstract: A gas turbine airfoil (10) includes a pressure sidewall (12) and a suction sidewall (14) joined along respective leading (16) and trailing edges (18) and extends radially outward from a root (20) to a tip (22). The airfoil also includes a trailing edge corner (24) comprising a metering hole (36) receiving a cooling fluid flow (26) from an interior fluid flow channel (e.g., 32) and discharging a metered flow (40). A dispersion cavity (42) receives the metered flow and discharges a dispersed flow (44). The dispersion cavity includes a cross sectional area (46) greater than a cross sectional area (48) of the metering hole. An open flow channel (52) receives the dispersed flow and conducts the dispersed flow to a periphery (54) of the airfoil, the open flow channel controlling mixing of the cooling fluid flow with a process gas (e.g., 28) flowing around an exterior (34) of the airfoil.