Abstract: Aspects of the invention relate to a fixture and a method to assist in the alignment of the inlet end of a transition duct and a combustor component in a turbine engine. The fixture includes a plurality of pressure transducers spaced on a mandrel so as to correspond to the target alignment location of the transition. The plurality of pressure transducers produce signals, which can be converted by a signal processor into an actual alignment location signal. A display can be provided for presenting graphical images of the target alignment location and the actual alignment location responsive to the actual alignment location signal received from the signal processor. Thus, a user can view the movement of the graphical image of the actual alignment location relative to the graphical image of the target alignment location such that the user can adjust the transition's position until the graphical images are substantially aligned.

Abstract: A steam transformer (200) receives steam through a steam inlet (203), and the steam is mixed in a mixing zone (231) with water entering through a water inlet (205). Steam cooled by contact with the water exits the steam transformer through a cold steam outlet (216). Between the mixing zone (231) and the cold steam outlet (216) is positioned a demister (214) that restricts the passage of water droplets. The steam transformer (200) is used to condition the steam temperature in steam turbine and combined cycle turbine facilities when adjustment of steam temperature is required, such as for cold starts of turbines. The steam transformer (200) may be installed into a bypass circuit or directly inline. A number of differing configurations and designs are disclosed.

Abstract: Embodiments of the invention relate to a system and method for non-destructively inspecting a component that is at least partially made of a composite material. In one embodiment, the composite component can be a ceramic matrix composite vane or a liner for a turbine engine. Aspects of the invention involve imaging the component using a magnetic resonance imaging (MRI) apparatus. To enhance the image, the component can be infiltrated with at least one contrast media, which can be in liquid or gas form. By imaging the component using the MRI apparatus, internal and/or external defects of the component can be revealed. In addition, internal and/or external features of interest can examined for dimensional accuracy, among other things.

Abstract: A nickel-based single crystal gas turbine component (30) having a low angle boundary (34) with improved material properties resulting from retained gamma/gamma prime eutectic phase at the low angle boundary. The coarse eutectic phase nodules roughen the grain boundary, reduce the slip distance and disperse concentrated planar slip in the vicinity of the boundary. As a result, the allowable angle of misorientation at the boundary may be increased to greater than 6° for the most highly stressed or critical areas of the component, thereby reducing the amount of scrap material and lowering the cost of manufacturing of a single crystal gas turbine component.

Abstract: A joint having bond line grains that nucleate in the joint region and grow into the adjoined solid substrates. The resulting bond line grains have a size that is greater than a thickness of a molten region. The surfaces of the substrates are cold worked to a desired degree of residual stress prior to the bonding process so that the recrystallization of the substrate surface necessary for the grains to grow into the substrates results in a reduction in the local free energy.

Abstract: An oil lift pocket for a bearing surface having a plurality of channels in communication with a supply port. The plurality of channels may be formed in a substantially bow shaped configuration. Each channel may extend from a supply port and terminate at an end and away from the supply port. The oil lift pocket greatly reduces friction in slow turning operations and reduces babbitt delamination, dead zones, and nonuniform support and lift as well.

Abstract: A turbine blade for a turbine engine having a cooling system in the turbine blade formed from at least one cooling channel. The cooling system may include one or more protrusions positioned in the cooling channel and including one or more vortex breakers along the length of the protrusion. The vortex breakers disrupt vortices formed downstream of the protrusions to increase heat transfer enhancement effect of the protrusions. The cooling channels of the cooling system may include a plurality of protrusions whose configuration is based upon the cooling requirements of the blade in which the cooling system is installed.

Abstract: A solid oxide fuel assembly is made, wherein rows (14, 25) of fuel cells (17, 19, 21, 27, 29, 31), each having an outer interconnection (20) and an outer electrode (32), are disposed next to each other with corrugated, electrically conducting expanded metal mesh member (22) between each row of cells, the corrugated mesh (22) having top crown portions and bottom portions, where the top crown portion (40) have a top bonded open cell nickel foam (51) which contacts outer interconnections (20) of the fuel cells, said mesh and nickel foam electrically connecting each row of fuel cells, and where there are no more metal felt connections between any fuel cells.

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 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: 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: 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 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 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 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.