Abstract: The present invention relates to monitoring the corrosive damage caused to items in a corrosive environment by using multiple monitored coupons 30 of varying thickness that, when corroded, transmit information to a monitor 40 allowing a user to estimate the corrosive damage valuable industrial components 20. The corrosion rate of the coupons 30 can be used to optimize the environmental conditions, so that items in the environment corrode at desired rates.

Abstract: A turbine blade for a turbine engine having a platform cooling system formed from one or more platform cooling channels extending from an inner cooling cavity in a root of a turbine blade to an outer surface of a platform on the turbine blade. The platform cooling channels may be positioned in ribs protruding from a bottom surface of the platform. The ribs act as fins during operation of a turbine engine in which the turbine blade is installed by increasing surface area of the platform and thereby increasing convection on the bottom surface.

Abstract: A tool for sensor management and fault visualization in machine condition monitoring. The method and system are able to monitor a plurality of sensors at one time. The sensors may be used in a power plant system monitoring system. The method and system may display a fault status for each sensor in the plurality of sensors in a single display, wherein the fault status for each sensor is displayed over time. The method and system also provide a mechanism that permits a user to examine details of each sensor in the plurality of sensors at any given time. In addition, the method and system are capable of categorizing each fault in the fault status using one or more properties or categorizing criteria. The method and system also permit sensors to be tested such that different operating models may be examined by utilizing different sensors.

Abstract: A composite material (10) formed of a ceramic matrix composite (CMC) material (12) protected by a ceramic insulating material (14). The constituent parts of the insulating material are selected to avoid degradation of the CMC material when the two layers are co-processed. The CMC material is processed to a predetermined state of shrinkage before wet insulating material is applied against the CMC material. The two materials are then co-fired together, with the relative amount of shrinkage between the two materials during the firing step being affected by the amount of pre-shrinkage of the CMC material during the bisque firing step. The shrinkage of the two materials during the co-firing step may be matched to minimize shrinkage stresses, or a predetermined amount of prestress between the materials may be achieved. An aluminum hydroxyl chloride binder material (24) may be used in the insulating material in order to avoid degradation of the fabric (28) of the CMC material during the co-firing step.

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 replaceable section (25) of force-cooling tubing assembly (21, 22) for attachment to a transition piece (5) of a gas turbine is comprised of two ends (54, 70) fashioned for attachment by removable unions (52) to adjoining parts of a force-cooling tubing assembly. When assembled thereto to complete the assembly, the replaceable section 25 provides for fluid communication between a manifold (3) and the transition piece (5) for either the supply or return of cooling fluid. A transition piece (5) in combination with two such assemblies, one a supply assembly (21), the other a return assembly (22), comprises a field-installable transition piece assembly (10) that provides for rapid and easy installation.

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 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: 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 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: 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 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 system and method for determining a connection between a one or more “from” connections points and one or more “to” connections points, wherein connections between the connection points are determined as a function of intermediate connections in the path formed between the “from” and “to” connection endpoints.

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: 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: 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: 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. An instructional assessment application includes a self-correct feature that marks an incorrect response as a self-corrected response based upon selection of the self-correct feature.

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.