Abstract: A non-conductive substrate being at least partially coated with a paint including reduced graphene oxide and a thermosetting polymer, the non-conductive substrate being directly coated by the paint, a method for the manufacture of this coated non-conductive substrate, methods for detecting leaks or strain deformation and the uses of said coated non-conductive substrate.

Abstract: A system for estimating both thickness and wear state of refractory material (1) of a metallurgical furnace (12), including at least on processor including a database of simulated frequency domain data named simulated spectra representing simulated shock waves reflected in simulated refractory materials of known state and thickness, each simulated spectrum being correlated with both known state and thickness data of the considered simulated refractory material, wherein the at least one processor is configured to record a reflected shock wave as a time domain signal, and to convert it into frequency domain data named experimental spectrum, and are further configured to compare the experimental spectrum with at least a plurality of simulated spectra from the database, to determine the best fitting simulated spectrum with the experimental spectrum and to estimate thickness and state of the refractory material (1) of the furnace (12) using known state and thickness data correlated with the best fitting simulated

Abstract: A non-conductive substrate being at least partially coated with a paint including reduced graphene oxide and a thermosetting polymer, the non-conductive substrate being directly coated by the paint, a method for the manufacture of this coated non-conductive substrate, methods for detecting leaks or strain deformation and the uses of said coated non-conductive substrate.

Abstract: A metallic substrate directly coated with a non-conductive primer, the non-conductive primer being at least partially coated with a paint, a method for the manufacture of this coated metallic substrate, a method for detecting strain deformation and the use the coated metallic substrate.

Abstract: An augmented reality (AR) device may identify a package in using a camera of the AR device. The AR device may identify a first corner of the package based on detecting differences in contrast, of a plurality of surfaces of the package, in a video feed generated by the AR device. The AR device may identify, based on identifying the first corner, a second corner of the package, a third corner of the package, and a fourth corner of the package. The AR device may determine a plurality of dimensions of the package. The AR device may transmit, to a shipping management platform, information identifying the plurality of dimensions, wherein the plurality of dimensions is to be used to generate a loading configuration for loading the package, along with a plurality of other packages, into a cargo container.

Abstract: The strip containing acaricide, is formed by a variety of compartments, placed in parallel and joined to each other, that serve to house an acaricide substance in semi-solid state, characterized in that the tube-shaped compartments, by their internal part will be: square, rectangular, cylindrical, hexagonal, or any geometrical shape and the inlet open at both ends, the inlet passage of less than 5 mm, within it, an acaricide substance is deposited, that acts by contact, the sizes of the containing strip, are ranging from 10 mm to 500 mm long, from 10 mm to 400 mm wide, from 1 mm to 5 mm high, the said limits included.

Abstract: An augmented reality (AR) device may identify a package in using a camera of the AR device. The AR device may identify a first corner of the package based on detecting differences in contrast, of a plurality of surfaces of the package, in a video feed generated by the AR device. The AR device may identify, based on identifying the first corner, a second corner of the package, a third corner of the package, and a fourth corner of the package. The AR device may determine a plurality of dimensions of the package. The AR device may transmit, to a shipping management platform, information identifying the plurality of dimensions, wherein the plurality of dimensions is to be used to generate a loading configuration for loading the package, along with a plurality of other packages, into a cargo container.

Abstract: A blade outer air seal (BOAS) includes an inner surface configured to contact a core airflow of a gas turbine engine having an axis. The BOAS also includes an outer surface. The BOAS also includes at least one rib extending in an axial direction along the outer surface and having a height in a radial direction that is at least twice as large as a width of the at least one rib in a circumferential direction.

Abstract: A turbine blade airfoil (32) with a center of mass (ACM) that is laterally offset from the center of mass (PCM) of a platform (42) to which the airfoil is attached. Respective offsets (da, dp) balance these centers of mass (ACM, PCM) about an attachment plane (64) of the blade root (30), providing balanced centrifugal loading on opposite lobes (51, 52) or other attachment surfaces of the root. The attachment plane (64) may be a plane of bilateral symmetry of the root, and/or it may include an attachment axis (65) that passes through the root center of mass (RCM) along a radius of rotation of the airfoil. The airfoil and platform centers of mass (ACM, PCM) may be dynamically balanced about the attachment axis (65) and/or the attachment plane (64).

Abstract: A turbine blade (110) is provided, where an exterior surface of the turbine blade (110) is exposed to a hot combustion gas (125) above a flow path line (141). The turbine blade (110) includes a trailing edge pin bank cooling channel (118) in an airfoil section (112), a cooling air supply channel (120) in a root section (114), and a channel (122) shaped with a radius of curvature (126), to extend the channel (122) across the flow path line (141) and interconnect the cooling air supply channel (120) to the trailing edge pin bank cooling channel (118). A width of the trailing edge pin bank cooling channel (118) is adjusted, such that the width at an inner diameter region (128) and an outer diameter region (131) is less than the width at an intermediate region (130) between the inner and outer diameter regions (128,131).

Abstract: A turbine blade airfoil (32) with a center of mass (ACM) that is laterally offset from the center of mass (PCM) of a platform (42) to which the airfoil is attached. Respective offsets (da, dp) balance these centers of mass (ACM, PCM) about an attachment plane (64) of the blade root (30), providing balanced centrifugal loading on opposite lobes (51, 52) or other attachment surfaces of the root. The attachment plane (64) may be a plane of bilateral symmetry of the root, and/or it may include an attachment axis (65) that passes through the root center of mass (RCM) along a radius of rotation of the airfoil. The airfoil and platform centers of mass (ACM, PCM) may be dynamically balanced about the attachment axis (65) and/or the attachment plane (64).

Abstract: Gas turbine engine seals and engines incorporating such seals are provided. In this regard, a representative seal includes: an annular seal body having an inner diameter and an outer diameter, the seal body extending along an axis of symmetry between a first end and a second end; the seal body being formed of a strip of material having first and second opposing edges, the strip of material being deformed to exhibit a first sealing surface at the first end, a second sealing surface at the second end, and a third sealing surface along the inner diameter, the first edge being located adjacent to the third sealing surface, the second edge being located adjacent to the second sealing surface; the first edge being spaced from the second edge to define an annular opening, the annular opening providing access to an annular cavity of the seal body.

Abstract: An example exit guide vane for a gas turbine engine is mounted adjacent to a diffuser case defining an air flow path. A thrust balance seal is attached to the diffuser and the exit guide vane is mounted adjacent the diffuser case for guiding air flow into the air flow path. The exit guide vane is mounted adjacent to the diffuser without interfering with the air flow path or restricting thermal expansion.

Abstract: A method of assembling a stator apparatus includes providing a first vane having an airfoil section located between a first platform section and a second platform section, positioning a first shroud ring adjacent to the first vane, welding the first platform section of the first vane to the first shroud ring relative to a first edge of the of the first platform section of the first vane, and welding the first platform section of the first vane to the first shroud ring relative to a second edge of the of the first platform section. The second edge is located opposite the first edge.

Abstract: Gas turbine engine seals and engines incorporating such seals are provided. In this regard, a representative seal includes: an annular seal body having an inner diameter and an outer diameter, the seal body extending along an axis of symmetry between a first end and a second end; the seal body being formed of a strip of material having first and second opposing edges, the strip of material being deformed to exhibit a first sealing surface at the first end, a second sealing surface at the second end, and a third sealing surface along the inner diameter, the first edge being located adjacent to the third sealing surface, the second edge being located adjacent to the second sealing surface; the first edge being spaced from the second edge to define an annular opening, the annular opening providing access to an annular cavity of the seal body.

Abstract: A method of assembling a stator apparatus includes providing a first vane having an airfoil section located between a first platform section and a second platform section, positioning a first shroud ring adjacent to the first vane, welding the first platform section of the first vane to the first shroud ring relative to a first edge of the of the first platform section of the first vane, and welding the first platform section of the first vane to the first shroud ring relative to a second edge of the of the first platform section. The second edge is located opposite the first edge.

Abstract: An example exit guide vane for a gas turbine engine is mounted adjacent to a diffuser case defining an air flow path. A thrust balance seal is attached to the diffuser and the exit guide vane is mounted adjacent the diffuser case for guiding air flow into the air flow path. The exit guide vane is mounted adjacent to the diffuser without interfering with the air flow path or restricting thermal expansion.