Abstract: A system and method for early detection of a failure of a gas turbine engine airfoil (10), such as but not restricted to a burn through of the airfoil outer skin (12). A sensor (52) provides a signal (54) responsive to a condition of fluid flowing through an outer cooling chamber (24) of the airfoil. A detected change in the condition of the fluid is correlated to a failure of the airfoil, which for example can be detected by measuring the static fluid pressure. An increase in the static pressure of fluid in the outer cooling chamber may indicate a breach in the region of the leading edge of the airfoil. A decrease in the static pressure of fluid in the outer cooling chamber may indicate a breach along other portions of the profile of the airfoil outer skin. Both pressure and temperature parameters of the fluid may be measured and coincident changes thereof correlated to a condition of failure of the airfoil.

Abstract: A thermal barrier layer (20) is formed by exposing an oxide ceramic material to a thermal regiment to create a surface heat affected zone effective to protect an underlying structural layer (18) of the material. The heat affected surface layer exhibits a lower strength and higher thermal conductivity than the underlying load-carrying material; however, it retains a sufficiently low thermal conductivity to function as an effective thermal barrier coating. Importantly, because the degraded material retains the same composition and thermal expansion characteristics as the underlying material, the thermal barrier layer remains integrally connected in graded fashion with the underlying material without an interface boundary there between.

Abstract: A gas turbine cycle that utilizes the vaporization of liquefied natural gas as an intercooler in an open loop gas turbine system. The system provides an increase in gas turbine cycle efficiencies while providing a convenient system for vaporizing liquefied natural gas. The systems and methods of the present invention permit the vaporization of liquefied natural gas using air that has been compressed in a first compressor, with the resulting cooled air being easier to compress and/or having fewer contaminants therein for compression in a second compressor. As the air is easier to compress, less energy is needed to operate the second compressor, thereby increasing the efficiency of the system. Additionally, unlike prior art systems that use water as an intercooler, no additional equipment is needed to cool the vaporized natural gas, such as cooling towers.

Abstract: A connector arrangement and techniques are provided for reducing eddy current losses and/or skin effects while enabling more readily serviceable series and phase connections between the coil ends 12 and 18 of a generator stator 10. This may be achieved by providing a connecting structure 24 that enables two parallel electrically conductive paths 26 and 28 that are electrically insulated from one another for passing a respective flow of electric current between the coil ends.

Abstract: A stator core module assembly (20) is provided which is adapted to be mounted to at least one structural element (16, 18) coupled to a stator frame (10). The stator core module assembly comprises a stator core module (22) adapted to form part of a stator core (21) and at least one keybar (32A, 32B) having a length less than a width of the stator core. The keybar may be coupled to the stator core module. The stator core module assembly further comprises at least one attachment member (34) for coupling the keybar to the structural element coupled to the stator frame.

Abstract: The present invention comprises a method and apparatus for installing a stator core into a power generator 1 that comprises assembling the stator core inside of a container 60, and then moving the container to the power generator. The container is horizontally aligned with the power generator, and the stator core is transferred from the container to the power generator.

Abstract: In one embodiment the present invention provides for a method for checking the alignment of a stator core that comprises placing a laser source 14 and a target 18 a given distance apart on a stator core 10 and activating the laser such that the laser strikes the target. Then measuring on the target where the laser strikes, and interpreting the measurement to determine any misalignment of the stator core in the given distance.

Abstract: A trailing edge attachment for a composite turbine airfoil. The trailing edge attachment may include an attachment device for attaching the trailing edge attachment to the airfoil. The attachment device may include a plurality of pins extending through the attachment device and into the trailing edge blade. The trailing edge attachment may also include a spanwise cooling channel for feeding a plurality of cooling channels extending between a leading edge of the trailing edge attachment and a trailing edge of the attachment device. The attachment device may be configured to place the leading edge of the composite airfoil in compression, thereby increasing the strength of the composite airfoil.

Abstract: A conformable layer (14) for inhibiting electrical discharge between vent tubes (16) and strands (12) in an inner-cooled coil (5). The conformable layer comprises a resistive inner core (24) and a conductive strip (20) wrapped in a conductive outer wrap (26). The conductive strip (20) is electrically connected to the strands (12) at one end of the coil (5) and left to electrically float at the other end. In this configuration, the conformable layer (14) reduces voltage buildup between the vent tubes (16) and the strands (12) to help prevent electrical damage to the coil (5).

Abstract: A system (10) for removing water from a flue gas (12) includes a heat exchanger (16) for receiving a flow of heat exchanging fluid and the flue gas (12). An absorber (40) may have a gas inlet (41) for receiving the flue gas (12) from the heat exchanger (16), an inlet (45) for receiving a desiccant solution and a media (42) receiving the desiccant solution for providing surface area contact between the flue gas (12) and the desiccant solution A dual cooler (26) may include a first side (27) through which a heat exchanging fluid and the desiccant solution may be directed for cooling. Valving (72) may be provided for alternating a flow of the heat exchanging fluid and a flow of the desiccant solution through the first side (27) of the dual cooler (26).

Abstract: An exhaust gas treatment apparatus (20) for reducing the concentration of NOx, HC and CO in an exhaust gas stream (18) such as produced by a gas turbine engine (12) of a power generating station (10). The treatment apparatus includes a multifunction catalytic element (26) having an upstream reducing-only portion (28) and a downstream reducing-plus-oxidizing portion (30) that is located downstream of an ammonia injection apparatus (24). The selective catalytic reduction (SCR) of NOx is promoted in the upstream portion of the catalytic element by the injection of ammonia in excess of the stoichiometric concentration, with the resulting ammonia slip being oxidized in the downstream portion of the catalytic element. Any additional NOx generated by the oxidation of the ammonia is further reduced in the downstream portion before being passed to the atmosphere (22).

Abstract: A rotor pole crossover connection joint for use in a rotating electrical machine is disclosed. The connection joint integrally couples a bottom rotor coil strap to a rotor pole crossover connector with a single piece connector that reduces, distributes or otherwise tolerates stress concentrations in the connector.

Abstract: A ceramic article having improved interlaminar strength and a method of forming the article. The article may be a ceramic matrix composite article. The methods of forming the articles increase the interlaminar strength of the article by forming indentations in the article during processing. The indentations may be tabs that are formed such that they provide one or more beneficial features for ceramic articles, such as CMC articles and hybrid structures. The tabs may be any of a variety of shapes, orientations, spacings, and combinations. In an alternative embodiment, the indentations are formed by pulling one or more fibers from one side of the ceramic layer to the other side. The articles have increased surface area, which helps to increase the bonding strength between the ceramic layer and any thermal barrier coating layer and/or ceramic core in the ceramic article.

Abstract: An optical measurement device for measuring strain related to deformation of a deformable surface of a component. The optical measurement device includes a fiber tension structure including opposing longitudinal end sections attached to the deformable surface. An optical fiber is tensioned by the fiber tension structure and includes a section defining a Bragg grating. The fiber tension structure includes a displaceable portion for forming a structural break between the longitudinal end sections where the fiber tension structure separates to form a gap between the first and second longitudinal end sections. The longitudinal end sections are movable independently of each other after formation of the structural break in the fiber tensioning structure.

Abstract: A barrier structure (302) blocks exit of spring clip fragments (317) that may break off from a spring clip assembly disposed between a gas turbine engine combustor (300) and a transition piece component (360). The barrier structure (302) may additionally comprise an aspect (326) effective to restrict a spring clip's (310, 311) radially inward compression, thereby reducing or eliminating damage to the spring clip (310, 311) during shipping and handling. The barrier structure (302) additionally may comprise an aspect (330) to restrict access by a human hand to the free ends (318) of the spring clips (310, 311). This aspect (330) reduces or eliminates the undesired lifting of the compressor by grabbing the spring clips (310, 311) during combustor transport, installation or removal. Accordingly, barrier structure embodiments are provided that reduce stress on spring clips, and that prevent the exit of spring clips from a containment space partly formed by the barrier structure.

Abstract: A gas turbine engine that includes a compressor, a combustion stage, a turbine assembly, a fuel gas feed system for supplying fuel gas to a combustion stage of the gas turbine, and an integrated fuel gas characterization system. The integrated fuel gas feed system can include a buffer tank. The integrated fuel gas characterization system for determining the amount of energy provided by the fuel prior to combustion of the fuel in the combustion stage. The integrated fuel gas characterization system minimizes megawatt swings by adjusting the operating parameters of the gas turbine engine based on the rate of change in fuel gas energy content. The integrated fuel gas characterization system also provides improved turbine engine start-up reliability by tuning the turbine engine operating parameters using fuel gas energy content measurements obtained prior to actual start-up.

Abstract: The present invention provides an apparatus for the horizontal stacking of laminations 10 and donuts to form a stator core. A stator generator frame 2 has multiple keybars 6 that run the axial length of the frame. The laminations 10 have grooves 12 there-in that engage the keybars to provide a secure fit of the laminations to the generator frame. By extending two or more of the keybars 6, these extensions 7 may be used as rails on which the laminations may be horizontally inserted into the stator frame.

Abstract: A method of forming a ceramic matrix composite (CMC) article (30) or a composite article (60) that minimizes the risk of delaminations while simultaneously maintaining a desired degree of porosity in the material. A pressure P applied against a surface of the article during a sintering process is controlled to be high enough to resist a separation force between the plies (66) of the CMC material (62) caused by anisotropic shrinkage of the material and/or to resist a separation force caused by differential shrinkage between the CMC material and an adjoined monolithic ceramic material (64). The pressure is also controlled to be low enough to avoid undue consolidation of the materials and to provide a desired degree of porosity in the sintered article. The pressure may be applied by delta-alpha tooling, and it may be varied verses the time of the sintering heating and/or across the article surface.

Abstract: System and computer program product 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: This invention relates to a seal plate system adapted to fit between axially adjacent turbine blades and turbine vanes to seal a rim cavity. The seal plate system may be formed from a seal plate supported by a plurality of extended disk lugs extending from a disk. The seal plate system may also include one or more extended disk lug receiving cavities adapted to receive protrusions extending from the disc. One or more ribs may extend from the seal plate for increasing the structural integrity of the seal plate.