Abstract: A first input to a mobile device indicates a first navigation destination at a first level of specificity. The mobile device initiates navigation towards a first location corresponding to the first navigation destination. While navigation towards the first location corresponding to the first navigation destination is ongoing and before reaching the first location, in accordance with a determination that one or more first criteria are satisfied, the mobile device prompts for an input for determination a second location corresponding to a second navigation destination with a second level of specificity, the second level of specificity more specific than the first level of specificity. The mobile device receives a second input in response to the prompt. In accordance with a determination that the second input satisfies one or more second criteria, the mobile device initiates navigation towards the second location corresponding to the second navigation destination.

Abstract: An integrally bladed rotor in which a hub and a web are formed from a fine grain microstructure using an investment casting process or from metal powder with a HIP process, and a plurality of rotor blades formed from a coarse grain microstructure using a metal additive manufacturing process, where the hub and the web and the rotor blades are formed as a single piece and from the same material.

Abstract: A technique for improving the thermal protection against oxidation for a component in a gas turbine engine, for example, blades, row 1 vanes and row 2 vanes. The technique includes spraying a thin layer of alloy 230 on a base substrate of the component at those locations on the component where thermal protection against oxidation is desired. A metal bond coat layer is then deposited on the alloy 230 layer and a thermal barrier coating is deposited on the bond coat layer. The chromium, molybdenum, iron and tungsten in alloy 230 provide superior oxidation resistance, and the addition of lanthanum in the alloy 230 helps tailor thermal expansion with the thermal barrier coating resulting in higher spallation life.

Abstract: Voids, cracks or other similar defects in substrates of thermal barrier coated superalloy components, such as turbine blades or vanes, are filled with resin, without need to remove substrate material surrounding the void by grinding or other processes. The resin is cured at a temperature under 200° C., eliminating the need for post void-filling heat treatment. The void-filled substrate and resin are then coated with a thermal barrier coating.

Abstract: A turbine blade having a squealer tip at a radially outer end of the turbine blade with a plurality of abradable coating cutting tips extending radially therefrom toward a ring segment is disclosed. During operation, the abradable coating cutting tips may cut into an abradable coating on the ring segments of the turbine engine that are positioned radially outward from the turbine blade. The plurality of abradable coating cutting tips may include one or more cutting arrises extending from the squealer tip to an outermost tip of the at least one of the abradable coating cutting tips.

Abstract: Computerized community-based social media moderation systems and methods. A method includes selecting, using instructions executed by a processor, a plurality of juror computing devices, outputting the social media post to the plurality of juror computing devices for review of the social media post in light of the standard of the online community, and receiving inputs regarding the social media post from the plurality of juror computing devices. If the inputs regarding the social media post from the plurality of juror computing devices meet a predetermined condition, the outputting of the social media post to the plurality of social media user computing devices belonging to the online community is disabled. The selecting of the plurality of juror computing devices is performed according to a randomizing operation.

Abstract: A system of layers in a protective coating (20) for a substrate (22), including at least an outer thermal barrier layer (32) and a tungsten bronze structure ceramic underlayer (30) that reduces spalling of the outer layer. The range of materials for the underlayer includes ceramics of the form Ba6?3mRe8+2mTi18O54, where 0<m<1.5, and Re is any rare earth element or mixture thereof. These underlayer materials reduce spalling of the thermal barrier layer, and thus extend the life of the coating system. In some embodiments, materials for the outer thermal barrier layer may include Yttria-stabilized Zirconia (YSZ) or ceramics with lower thermal conductivity than YSZ. A segmented YSZ layer (26) is provided in some embodiments for additional thermal expansion compliance.

Abstract: Voids, cracks or other similar defects in substrates of thermal barrier coated superalloy components, such as turbine blades or vanes, are filled with resin, without need to remove substrate material surrounding the void by grinding or other processes. The resin is cured at a temperature under 200° C., eliminating the need for post void-filling heat treatment. The void-filled substrate and resin are then coated with a thermal barrier coating.

Abstract: A method for welding to a superalloy material without causing cracking of the material. The method includes the steps of depositing a weld strip (18) of a weldable material onto a superalloy substrate material (12) using a spray deposition process (20) and then forming a weldment (26) to the weld strip. None or a controlled amount of the substrate material (12) is melted during the weld in order to maintain the concentration of strengthening elements in the local melt within a zone of weldability. The spray deposition process may be a thermal process such as HVOF or a cold spray process. A groove (16) may be formed in a surface (10) of the superalloy substrate material to receive the weld strip. A diffusion heat treatment step may be used to improve adhesion between the weld strip and the superalloy material.

Abstract: A squealer tip preform having a coating including an abrasive is disclosed. The squealer tip may be separately formed from a generally elongated blade to which the squealer tip preform is configured to be attached. The squealer tip may be configured such that an outer surface of the squealer tip preform is generally aligned with an outer side surface of the turbine blade defining a cross-sectional profile of the turbine blade. Forming the squealer tip preform with an abrasive coating separate from the turbine blade greatly reduces costs and improves efficiency as compared with conventional systems.

Abstract: A system of layers in a protective coating (20) for a substrate (22), including at least an outer thermal barrier layer (32) and a tungsten bronze structure ceramic underlayer (30) that reduces spalling of the outer layer. The range of materials for the underlayer includes ceramics of the form Ba6?3mRe8+2mTi18O54, where 0<m<1.5, and Re is any rare earth element or mixture thereof. These underlayer materials reduce spalling of the thermal barrier layer, and thus extend the life of the coating system. In some embodiments, materials for the outer thermal barrier layer may include Yttria-stabilized Zirconia (YSZ) or ceramics with lower thermal conductivity than YSZ. A segmented YSZ layer (26) is provided in some embodiments for additional thermal expansion compliance.

Abstract: Fabricating a turbine component (50) by casting a core structure (30), forming an array of pits (24) in an outer surface (32) of the core structure, depositing a transient liquid phase (TLP) material (40) on the outer surface of the core structure, the TLP containing a melting-point depressant, depositing a skin (42) on the outer surface of the core structure over the TLP material, and heating the assembly, thus forming both a diffusion bond and a mechanical interlock between the skin and the core structure. The heating diffuses the melting-point depressant away from the interface. Subsurface cooling channels (35) may be formed by forming grooves (34) in the outer surface of the core structure, filling the grooves with a fugitive filler (36), depositing and bonding the skin (42), then removing the fugitive material.

Abstract: A method of measuring a thickness of a coating on a substrate material. A first pulse of monochromatic light having a predetermined first wavelength is emitted toward the coating and substrate material. A second pulse of monochromatic light having a predetermined second wavelength is emitted toward the coating and substrate material, the second wavelength being different than the first wavelength. A first elapsed time is measured from emission of the first pulse of light to reception of a reflection of the first pulse of light from a surface of the substrate material at an interface with the coating. A second elapsed time is measured from emission of the second pulse of light to reception of a reflection of the second pulse of light from an outer surface of the coating. A thickness of the coating is determined as a function of a difference between the first and second elapsed times.

Abstract: A squealer tip preform having a coating including an abrasive is disclosed. The squealer tip may be separately formed from a generally elongated blade to which the squealer tip preform is configured to be attached. The squealer tip may be configured such that an outer surface of the squealer tip preform is generally aligned with an outer side surface of the turbine blade defining a cross-sectional profile of the turbine blade. Forming the squealer tip preform with an abrasive coating separate from the turbine blade greatly reduces costs and improves efficiency as compared with conventional systems.

Abstract: Fabricating a turbine component (50) by casting a core structure (30), forming an array of pits (24) in an outer surface (32) of the core structure, depositing a transient liquid phase (TLP) material (40) on the outer surface of the core structure, the TLP containing a melting-point depressant, depositing a skin (42) on the outer surface of the core structure over the TLP material, and heating the assembly, thus forming both a diffusion bond and a mechanical interlock between the skin and the core structure. The heating diffuses the melting-point depressant away from the interface. Subsurface cooling channels (35) may be formed by forming grooves (34) in the outer surface of the core structure, filling the grooves with a fugitive filler (36), depositing and bonding the skin (42), then removing the fugitive material.

Abstract: A method of making a combustion turbine component includes thermal spraying a transient liquid phase (TLP) forming layer onto a combustion turbine component substrate and thermal spraying a main material layer onto the TLP forming layer. The combustion turbine component substrate, TLP forming layer, and main material layer are heat treated to thereby bond the main material layer to the combustion turbine component substrate.

Abstract: A method of measuring a thickness of a coating on a substrate material. A first pulse of monochromatic light having a predetermined first wavelength is emitted toward the coating and substrate material. A second pulse of monochromatic light having a predetermined second wavelength is emitted toward the coating and substrate material, the second wavelength being different than the first wavelength. A first elapsed time is measured from emission of the first pulse of light to reception of a reflection of the first pulse of light from a surface of the substrate material at an interface with the coating. A second elapsed time is measured from emission of the second pulse of light to reception of a reflection of the second pulse of light from an outer surface of the coating. A thickness of the coating is determined as a function of a difference between the first and second elapsed times.

Abstract: A bimetallic bond layer (26, 28) for a thermal barrier coating or TBC (30) on a superalloy substrate (22) for a high temperature environment. An interlayer (26) is applied on the substrate. A bond coat (28) comprising a CoNiCrAlY or NiCoCrAlY alloy is applied on the interlayer. A ceramic TBC (30) such as 8YSZ is applied on the bond coat. The interlayer (26) is an alloy that is compatible with the substrate and the bond coat, and that blocks or delays diffusion of aluminum from the bond coat into the substrate at high operating temperatures. This preserves aluminum in the bond coat that maintains a beneficial alumina scale (29) between the bond coat and the TBC. This delays spalling of the TBC, and lengthens the coating and component life.

Abstract: A quantity of particles (28) may be cold-sprayed toward the distal surface (22) of a turbine blade (6) at a temperature below a melting point of the particles at a velocity sufficiently high to cause at least a portion of the particles to adhere to the surface to form squealer ridge (24) with a desired cutting profile. The cutting profile may be defined by a face (52) and a land (54) disposed at a relief angle (38) relative to a direction of motion (58) of a cutting edge (48). The ridge may be built by multiple passes of a cold spray gun depositing sequential layers (30, 32, 34) of varying widths. An in-service blade having worn distal surface may be repaired using this technique.