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 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: 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 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: 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: 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 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: 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: An interconnecting assembly (100) for a rotor assembly of a dynamoelectric machine is provided. The interconnecting assembly may be part of an electrically conductive path generally extending from a radially inward section of the rotor assembly to a top winding of a stacked winding (128) located at a radially outward section of the rotor assembly. The interconnecting assembly may include a first connecting member (106) connected to a radial lead (104) at the inward section of the rotor assembly. This first connecting member is made up of multiple conductive leaves and includes a flexible bend (108) positioned to provide a resilient-connection relative to at least a radial direction. The interconnecting assembly may further include a second connecting member (124) mechanically connected to the first connecting member by way of the resilient connection. This second connecting member is electrically connected to the first connecting member and to the top winding.

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 (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.

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 turbine blade for a turbine engine having an internal cooling system formed from at least one cavity for receiving cooling air from a turbine blade assembly, passing the cooling air through the internal cooling system, and expelling the cooling air through orifices in a leading edge forming a showerhead, orifices in a trailing edge and in other locations. The showerhead includes exhaust orifices extending at various angles relative to each other through an outer wall forming the turbine blade. The exhaust orifices may form rows of orifices that are offset generally orthogonally and generally parallel to a longitudinal axis of the blade. The exhaust orifices are configured to effectively cool the leading edge portion of the blade and to reduce the likelihood of cracking of the outer wall forming the leading edge.

Abstract: A system, method and computer program product for real-time observation assessment is provided. The invention, designed for educators, takes advantage of handheld computers, desktop/laptop computers and the increasing presence of Internet access in order to reduce the paperwork associated with conventional educational assessments. The invention includes an array of instructional assessment applications designed to run on handheld computers. The instructional assessment applications may be based on existing and widely-used paper methodologies. A common Web-based platform for assessment application distribution, selection, download, data management and reporting is also provided. Users can then periodically synchronize instructional data (assessments, diagnostic results, notes and/or schedules) to the Web site. At the Web site, browser-based reports and analysis can be viewed, administered and shared via electronic mail.

Abstract: A ceramic insulating composition including monoclinic zirconia-hafnia. The zirconia-hafnia may be used as a filler powder (14) in a ceramic composition (10), or it may be used as a protective overlayer (50). The zirconia-hafnia (24) may be combined with alumina (22) to achieve a desired elastic modulus. The portion of hafnia contained in the zirconia-hafnia is selected to provide a predetermined phase transition temperature to minimize undesired phase changes during high temperature use of the material.

Abstract: Aspects of the invention relate to a method for facilitating the reduction of carbon monoxide emissions during part load operation of a turbine engine by holding high combustor temperatures. The combustor section of the turbine engine includes a plurality of combustors, each combustor having a pilot nozzle, a plurality of main nozzles circumferentially surrounding the pilot nozzle, and a premix ring. According to one aspects of the invention, a first pair of combustors are selected. Fuel can be substantially restricted from being supplied to the main nozzles and the premix ring of the selected combustors, while fuel continues to be supplied to the pilot nozzles of the selected combustors. Additional combustors can be selected and the supply of fuel can be selectively restricted as described above. The process can continue until there is substantially zero net power out of the engine.