Abstract: A poker card game and apparatus and software for its play are disclosed, particularly adapted for casino play, in which each player in a given game, using only a single dealt hand, plays simultaneously separately against the dealer (the house) and against the other players. Betting for the two lines of play may be separate or linked, and a player can elect to play only against the dealer or to play both games together. The game is played as a form of five-card stud with betting before each deal. At the end of each game a player's status as to whether he/she beat the dealer, beat the other players or both is determined and displayed, and winners are paid accordingly. Conventional dealing may be used, but it is preferred that a biased deal, which enhances the opportunities for players to be dealt reasonably good poker hands, be used.

Abstract: A method for posting and responding to a query is provided for enabling a first user to input the query to a system, converting the query to a hyperlink, adding the hyperlink to an interactive ticker for response, and enabling a second user to select a query from the ticker and respond to the first user by at least one of e-mail, instant message, and message board post.

Abstract: Techniques for real-time observation assessment are provided. The techniques, which are designed for educators, take advantage of handheld computers, desktop/laptop computers and Internet access in order to reduce the paperwork associated with conventional educational assessments. An array of instructional assessment applications are 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: An apparatus and method for determining terminal solid solubility temperature in materials capable of forming hydrides, such as reactor pressure tubes. An inspection device is positioned within the reactor pressure tube under test and a pair of annular seals are radially deployed to seal a section of the pressure tube. Any water within the sealed section is displaced through the injection of gas and the heating of the sealed section to dry the tube and the device. A probe assembly on the device is deployed to contact the interior surface of the pressure tube and measure resistivity changes in the pressure tube wall as a function of temperature. The probe assembly includes a thermocouple probe for measuring temperature and transmit and receive coils for inducing eddy currents within the pressure tube wall. The pressure tube is allowed to cool at a predetermined rate, is reheated at a predetermined rate, and is allowed to cool again.

Abstract: A fluid fill/storage/overflow reservoir/tank suitable for use with, for example, a liquid cooled engine, includes a clip-in provision for an oil stick tube that does not require removal of the oil stick tube from an engine assembly upon removal of the fluid fill/storage/overflow reservoir/tank from the engine assembly.

Abstract: Embodiments of the present invention provide resonators (260, 460) that have lateral walls (268, 270) disposed at non-square angles relative to the liner's longitudinal (and flow-based) axis (219) such that a film cooling of substantial portions of an intervening strip (244, 444) is provided from apertures (226A, 226B, 426) in a resonator box (262, 462) adjacent and upstream from the intervening strip (244, 444). This film cooling also cools weld seams (280) along the lateral walls (268, 270) of the resonator boxes (262, 462). In various embodiments the lateral wall angles are such that film cooling may be provided to include the most of the downstream portions of the intervening strips (244, 444). These downstream portions are closer to the combustion heat source and therefore expected to be in greater need of cooling.

Abstract: A configuration of seals disposed around and between a plurality of ring segments (10) arrayed annularly about the periphery of moving blades in a gas turbine engine. The seals function to retain coolant in the plenum (18) within each of the ring segments (10). The seals are disposed atop a substrate (16A), which forms the top of the plenum (18). The first seal (25) is made of a piece of sheet material and seals the gap between adjacent ring segments. This seal has an edge (25A) thereof creased for mating with a similar seal on an adjacent ring segment. A second seal (27), which is also made of sheet material, seals the ends of the plenum (18) of the ring segments (10). Lastly, a third seal (29), which is also made of a piece of sheet material, seals the sides of the second seal (27).

Abstract: A hybrid cast component (10) including both a columnar grained region (12) and a single crystal region (14) integrally formed and joined along a metallurgical boundary (32) in a single casting operation without the need for any weld or braze. A gas turbine blade formed as such may include a columnar grained airfoil and a single crystal platform without any necessity for a thermally formed joint at the blade fillet area.

Abstract: A gas turbine ring segment (10) for use in gas turbine engines made from a ceramic matrix composite (CMC) material is disclosed. The ring segment includes a stacked multiplicity of CMC thin-sheet lamellae (25a, 25b) each comprising a peripheral surface collectively defining a cross-section profile of the ring segment. The lamellae collectively define a channel (11) formed in the center thereof for receiving a bow-tie member (27). The bow-tie member is disposed in the channel for holding together the stacked lamellae in a through thickness direction, and the in-plane strength of the bow-tie member is perpendicular to the in-plane strength of the lamellae. A stem portion (33) of the assembly may be further secured with a wrap (38) of CMC ribbon.

Abstract: A combustion turbine component (10) includes a combustion turbine component substrate (16) and an alloy coating (14) on the combustion turbine component substrate. The alloy coating (14) includes a first amount, by weight percent, of nickel (Ni) and a second amount, by weight percent, of cobalt (Co), the first amount being greater than the second amount. The alloy coating also includes chromium (Cr), aluminum (Al), and yttrium (Y). The alloy coating further includes at least one of titanium (Ti), tantalum (Ta), tungsten (W), and rhenium (Re). Moreover, the alloy coating includes at least one rare earth element, and an oxide of at least one of the yttrium the at least one rare earth element.

Abstract: A method for maintaining a system consisting of a plurality of components, comprises the steps of collecting maintenance information for each component of the system for which maintenance information is available; providing a maintenance schedule for components of the system; operating the system; and maintaining the system wherein during scheduled maintenance of a component information about the status of that component is acquired, during a failure of a component information about the failure of that component is acquired, and modifying the maintenance schedule according to the acquired information.

Abstract: A combustion turbine component (10) includes a combustion turbine component substrate (16) and an alloy coating (14) on the combustion turbine component substrate. The alloy coating (14) includes a first amount, by weight percent, of cobalt (Co) and a second amount, by weight percent, of nickel (Ni), the first amount being greater than the second amount. The alloy coating further includes chromium (Cr), aluminum (Al), at least one rare earth element, and an oxide of the at least one rare earth element.

Abstract: A gas turbine engine is provided comprising an outer shell, a compressor assembly, at least one combustor assembly, a turbine assembly and duct structure. The outer shell includes a compressor section, a combustor section, an intermediate section and a turbine section. The intermediate section includes at least one first opening and at least one second opening. The compressor assembly is located in the compressor section to define with the compressor section a compressor apparatus to compress air. The at least one combustor assembly is coupled to the combustor section to define with the combustor section a combustor apparatus. The turbine assembly is located in the turbine section to define with the turbine section a turbine apparatus.

Abstract: A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane.

Abstract: This document discusses, among other things, systems, devices, and methods of disabling an automatic generator starting (AGS) actuator, such as used with a fuel-powered AC power generator providing AC electrical power to a recreational vehicle (RV) or other vehicle. The AGS actuator is disabled in response to a fault condition, such as may be indicative of a risk of hazardous gas, such as carbon monoxide (CO) accumulating near the vehicle, potentially in an enclosed area. After such disabling is performed, the vehicle driver would then have to consciously re-engage the AGS actuator. Factors useful for determining whether the fault condition exist include, among other things, transmission position, wheel rotation, vehicle engine operation status, ignition status, and/or an exhaust gas sensor.

Abstract: A multi-stage selective catalytic reduction (SCR) unit (32) provides efficient reduction of NOx and other pollutants from about 50-550° C. in a power plant (19). Hydrogen (24) and ammonia (29) are variably supplied to the SCR unit depending on temperature. An upstream portion (34) of the SCR unit catalyzes NOx+NH3 reactions above about 200° C. A downstream portion (36) catalyzes NOx+H2 reactions below about 260° C., and catalyzes oxidation of NH3, CO, and VOCs with oxygen in the exhaust above about 200° C., efficiently removing NOx and other pollutants over a range of conditions with low slippage of NH3. An ammonia synthesis unit (28) may be connected to the SCR unit to provide NH3 as needed, avoiding transport and storage of ammonia or urea at the site. A carbonaceous gasification plant (18) on site may supply hydrogen and nitrogen to the ammonia synthesis unit, and hydrogen to the SCR unit.

Abstract: A locking spacer assembly for filling a void between adjacent components in a turbine engine. In at least one embodiment, the locking spacer assembly may be configured to be inserted between adjacent turbine blades in a disc groove in a turbine blade stage assembly. The locking spacer assembly may be formed from fore and aft end supports and a locking device having fore and aft angled surfaces for urging the fore and aft end supports into lateral recesses in the disc groove. The locking spacer assembly may also include a mid spacer positioned between the fore and aft end supports. A retainer may be attached to the locking device to draw the fore and aft angled surfaces of the locking device into contact with the fore and aft support surfaces and urge the first and second end supports into lateral recesses in the disc groove.

Abstract: A cooling system for a turbine blade of a turbine engine having multiple serpentine trailing edge cooling channels in parallel. The serpentine cooling channels are positioned proximate to a trailing edge of the turbine blade and facilitate increased heat removal with less cooling fluid flow, thereby resulting in increased cooling system efficiency.

Abstract: A means (22) for structurally stiffening or reinforcing a ceramic matrix composite (CMC) gas turbine component, such as an airfoil-shaped component, is provided. This structural stiffening or reinforcing of the airfoil allows for reducing bending stress that may be produced from internal or external pressurization of the airfoil without incurring any substantial thermal stress. The stiffener is disposed on a CMC wall and generally extends along a chord length of the airfoil.

Abstract: Aspects of the invention relate to a system and method for actively controlling compressor clearances in a turbine engine by passing a thermal fluid in heat exchanging relation through a compressor vane carrier. During some operational conditions, such as hot restart or spin cool, it may be desirable to heat the vane carrier to enlarge or at least prevent a decrease in compressor clearances. In such cases, a heated thermal fluid can be provided by reclaiming residual exhaust energy from a heat recovery steam generator. At any condition where improved performance is desired, such as at base load operation, the vane carrier can be cooled to minimize compressor clearances. A cooled thermal fluid can be bleed air from an upstream portion of the compressor, water-cooled high pressure bleed air from a downstream portion of the compressor, or feed water from the bottoming cycle in a combined cycle engine.