Abstract: A composite turbine disc includes a high nickel rim section and a steel bore section. The rim section is formed from a high nickel alloy which provides a higher melting point as compared to the material used for the bore section. A plating or forged welding enhanced agent layer is disposed between the bore section and rim section. Composite disc can be formed by forging the rim and bore material together, or by welding the rim and bore material together.

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: Aspects of the invention relate to a system for reducing stagnation between substantially adjacent components while providing enhanced heat distribution properties in the corners and edges of the components. Each component is generally hollow and has two walls disposed substantially orthogonal to each other. Each of the two walls includes a substantially planar region, having an associated thickness, that transitions into a corner region. The two walls join in the corner region to form an outer edge portion and an inner edge portion. The interior surface of each wall in the corner region approaches the exterior surface as the interior surface advances toward the inner edge portion such that the thickness in the corner region does not exceed the thickness of the substantially planar region. The components are substantially adjacent such that the outer edge portions are disposed opposite and substantially parallel to each other.

Abstract: A flux probe (100) for measuring the rotor flux of an electric generator (10). The probe (100) is affixed to a probe carrier (102) and held within a stator coil slot (62) by affixing the carrier (102) to two opposing grooves (104) formed in sidewalls (81) of the slot (62). One or more stator coils (18) are also disposed in the slot (62) and retained therein by a wedge (74) and corresponding spring (72) that applies an radially outwardly directed force to the coils (18). In one embodiment the probe carrier (102) is affixed to a radially inwardly directed face (82) of the wedge (74).

Abstract: A catalytic gas turbine includes a compressor, a catalytic combustor, a turbine, and a flow path conducting a bypass portion of the compressed air around the combustor and turbine. A method of operating the catalytic gas turbine to activate a catalyst in the catalytic combustor includes opening an inlet guide vane upstream of the compressor to a position to produce an increased volume of compressed air. The increased volume exceeds a volume of compressed air needed to support combustion. A bypass portion of the compressed air is extracted and directed around the combustor and turbine. The method may also include extracting a recirculation portion of the compressed air and directing the recirculation portion into the inlet of the compressor.

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: Aspects of the invention relate to a turbine engine system and method for actively managing blade tip clearances during part load operation of the engine. Aspects of the invention relate to extracting a portion of the combustion gases from the combustor section of the engine and routing these heated gases to the blade rings or other stationary structure surrounding the turbine blades. Upon exposure to the combustion gases, which can be mixed with compressor exit air, the stationary structure will thermally expand, causing blade tip clearances to increase. Thus, concerns of blade tip rubbing are minimized. Once the engines achieves steady state operation, the flow of the combustion gases to the blade rings can be substantially restricted so that only compressor exit air is supplied to the stationary structure. Consequently, the stationary structure will contract and the blade tip clearances will decrease, thereby increasing the efficiency of the turbine.

Abstract: A header (10) for use with an inner-cooled half coil (13) in a stator phase winding of an electrical generator. The half coil may include a stack of cooling tubes (16,18) with a first stack of conductive strands (20, 22, 24, 26) adjacent a first side of the stack of cooling tubes and a second stack of conductive strands (20, 22, 24, 26) adjacent a second side of the stack of cooling tubes. A header (10) is conductively bonded (92) by brazing to each strand of the first stack of conductive strands (20, 22, 24, 26) and to each strand of the second stack of conductive strands (20, 22, 24, 26) for consolidating the first and second stacks of conductive strands. A means (34, 36) for allowing a coolant to flow through the header (10) may be provided to allow coolant to flow through the stack of cooling tubes (16, 18).

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: Aspects of the invention relate to resonator assemblies for use in non-uniform flow environments. The resonator assemblies include one or more features, such as a box or a scoop, for substantially equalizing the pressure on the resonator. In the box configuration, a box is attached on top of the resonator. The box has a top plate with a plurality of openings and at least one side wall extending from the entire periphery of the top plate. A plenum is defined between the box and the resonator plate. In the scoop configuration, a scoop is attached to the top of the resonator such that the scoop substantially overhangs the resonator. The scoop includes at least one side wall extending substantially perpendicularly therefrom, except for one side without a side wall so as to provide an opening into a space defined between the scoop and the resonator.

Abstract: The present invention provides for a fitted wedge wherein a formed outer frame is loosely fitted into a desired gap. The formed outer frame contains a lateral gap such that the formed outer frame is substantially or completely divided into two halves. A thin, stiff sheet coated with a resin saturated felt is then inserted between the two halves of the outer frame. The two halves are pushed apart, snuggly fitting the formed outer frame into place. The resin in the felt is then cured, forming a single, snuggly fit wedge.

Abstract: An inspection carriage provides for remote inspection of the Z-shroud and snubber regions of the blades of a steam turbine, while the blades remain in the turbine. The carriage includes a non-destructive inspection probe such as a meandering wave magnetometer probe or eddy current probe mounted on a slider, so that the probe may be moved along a radial axis, skew axis, axial axis, and rotation axis. Cameras are provided on the carriage so that the probe may be remotely guided into the region to be inspected.

Abstract: A exemplary method of depositing a coating on a substrate using a spray process is provided that may include selecting a desired dominant feature (62) for the coating and controlling the spray process (64, 68) to have at least one of an in-flight particle temperature distribution and an in-flight particle velocity distribution predicted to produce the dominant feature. One aspect allows for adjusting (64, 68) the at least one distribution to cause the distribution to shift from an in-flight Gaussian particle distribution to an in-flight non-Gaussian particle distribution. It may be determined whether the dominant feature for the coating is deposited within acceptable limits (66) and adjusting the at least one in-flight particle distribution (68) if the dominant feature for the coating is not deposited within acceptable limits. One aspect allows for depositing on the substrate a spray jet of particles having a bimodal distribution of particle temperature and a bimodal distribution of particle velocity.

Abstract: An airfoil (30) having a continuous layer of ceramic matrix composite (CMC) material (34) extending from a suction side (33) to a pressure side (35) around a trailing edge portion (31). The CMC material includes an inner wrap (36) extending around an inner trailing edge portion (38) and an outer wrap (40) extending around an outer trailing edge portion (42). A filler material (44) is disposed between the inner and outer wraps to substantially eliminate voids in the trailing edge portion. The filler material may be pre-processed to an intermediate stage and used as a mandrel for forming the outer trailing edge portion, and then co-processed with the inner and outer wraps to a final form. The filler material may be pre-processed to include a desired mechanical feature such as a cooling passage (22) or a protrusion (48).

Abstract: An insulating ceramic made up of a plurality of partially filled shapes (e.g., 101), such as oblate spheroids, spheres, and shapes free of corners, is provided. Each partially filled shape may include an inner skeleton (e.g., 102) and an outer skin (e.g., 104). The inner skeleton may be stabilized at a higher temperature relative to the outer skin. The shapes may be disposed in a binding matrix. The thickness of the outer skin may be very thin in view of the support provided by the inner skeleton, thereby improving the abradability characteristics of the ceramic.

Abstract: A material (100) formed of a sintered aggregation of ceria particles (106), mullite particles (108) and an alumina matrix material (110). Differential thermal expansion of the ceria and mullite particles generates thermal stress sufficient to create micro-cracking of the ceria particles. The ratio of ceria to mullite may be selected to achieve a desired coefficient of thermal expansion for matching the thermal growth of a mating CMC material (102). The micro cracks provide the material with a desired degree of strain tolerance useful in high temperature applications such as a solid core gas turbine vane (20).

Abstract: An eddy current inspection probe provides multiple interchangeable configurations for enabling an inspector to reach most or all portions of most or all turbine blades within a combustion turbine by inserting the probe through an inspection port, without disassembling the turbine. The probe shaft contains the electronic signal wire for the inspection tip and a port for a video probe, thereby facilitating use of the video probe and protecting these components. The inspection tip connector at the end of the main shaft is pivotally secured to the shaft, and may be set at any desired angle by using a semirigid or rigid member passing through the shaft, and connected to lever within the handle. Any one of a plurality of probe tips and shaft extensions may be selected to configure the inspection probe to reach a desired location within the turbine.

Abstract: A method and apparatus for calibrating an acoustic thermography system 10 and/or enhancing the flaw detection abilities of such a system is provided. The method allows applying a material (e.g., 103) to a specimen 12 undergoing acoustic thermography inspection. The material is thermally responsive to acoustic energy transmitted to the specimen by the acoustic thermography system. In one aspect thereof, a thermal response of the material applied to the specimen when subjected to acoustic energy is processed to determine whether the level of acoustic energy applied by the acoustic thermographic system appropriately meets a desired amount of acoustic energy for inspecting the specimen. In another aspect thereof, the thermal response of the specimen in combination with the applied material may be processed to determine whether certain types of flaws (e.g.

Abstract: A system (10) for imaging a rotating turbine blade (20) includes an image projector (12) receiving a moving image of the rotating blade and projecting a movement-compensated image. The system also includes an image receptor (14) for receiving the movement-compensated image. A sensor (16) is provided for generating information (28) indicative of a velocity of the rotating turbine blade and a processor (18) generates a drive signal (30) responsive to the information for controlling a position of the image projector. The image projector is controlled to receive the moving image at a desired angular position and to project the movement-compensated image to the image receptor so that the movement-compensated image appears stationary relative to the image receptor.

Abstract: Aspects of the invention relate to a compressor system for a turbine engine that not only provides large compressor seal clearances as the engine passes through non-standard operating conditions, but also minimizes the clearances during normal engine operation, thereby increasing the efficiency of the compressor. In one embodiment, a substantially annular seal land is secured at one end to an annular extension arm on a compressor disk. When the engine reaches steady state operation, the non-attached end of the seal land can extend radially outward to reduce the clearance between the seal land and a shroud extending over the ends of the adjacent stationary airfoils. The seal land can be designed to resist the rotational forces imparted by the turning rotor until a certain desired operating condition is reached. In one embodiment, the seal land reaches full extension when the engine is operating at about 3600 rpm.