Abstract: During a manufacture method, a component is scanned using a CT machine. The component includes a first member and a second member. The first member includes a first member aperture extending through the first member to the second member. Aperture data is determined for the first member aperture based on scan data. A centerline vector is determined for the first member aperture. The determining of the centerline vector includes fitting a geometric primitive to the aperture data to describe at least a portion of the scanned outer perimeter geometry of the first member aperture. The centerline vector for the first member aperture is determined based on a centerline vector of the geometric primitive and/or a center point of the geometric primitive. A point of intersection between the centerline vector and a reference plane is determined. A second member aperture is formed in the second member according to a formation operation.

Abstract: A method of manufacture is provided during which a component is scanned using a computed tomography machine to provide scan data. The component includes a first member and a second member. A first member aperture extends through the first member to the second member. Aperture data is determined for the first member aperture based on the scan data. A center of the scanned geometry is located. An eigen vector is determined for the scanned geometry at the center. An exterior point of intersection between an exterior surface of the second member and an axis is located. The axis is coincident with the center and determined using the eigen vector. A second member aperture is formed in the second member according to a formation operation that aligns the second member aperture being formed with the first member aperture in the first member.

Abstract: In at least one embodiment, a system for a re-entry tool to be used with oilfield equipment is disclosed. A stinger that includes flushing holes to enable fluid for flushing through the re-entry tool and into one or more of an Xmas tree head, tubing hanger, or crown plug, is provided in the system. The system includes one or more sleeves external to the stringer. The one or more sleeves include flushing slots to enable circulation of the fluid from the Xmas tree head, tubing hanger, or crown plug to an external environment relative to the Xmas tree head.

Abstract: In at least one embodiment, a system for a re-entry tool to be used with oilfield equipment is disclosed. A stinger that includes flushing holes to enable fluid for flushing through the re-entry tool and into one or more of an Xmas tree head, tubing hanger, or crown plug, is provided in the system. The system includes one or more sleeves external to the stringer. The one or more sleeves include flushing slots to enable circulation of the fluid from the Xmas tree head, tubing hanger, or crown plug to an external environment relative to the Xmas tree head.

Abstract: A manufacturing method is provided. During this method, a preform component for a turbine engine is provided that includes a substrate. A meter section of a cooling aperture is formed in the substrate. An external coating is applied over the substrate. At least a portion of the substrate and the external coating is scanned with an imaging system to provide scan data indicative of an internal structure of the portion of the substrate and the external coating. A diffuser section of the cooling aperture is formed in the external coating and the substrate based on the scan data.

Abstract: A manufacturing method is provided. During this method, a preform component for a turbine engine is provided that includes a substrate. A meter section of a cooling aperture is formed in the substrate. An external coating is applied over the substrate. At least a portion of the substrate and the external coating is scanned with an imaging system to provide scan data indicative of an internal structure of the portion of the substrate and the external coating. A diffuser section of the cooling aperture is formed in the external coating and the substrate based on the scan data.

Abstract: The invention provides a skid steer rake capable of adjustment and modulation during use, without any need to halt operation of attached machinery. The skid steer rake is configured with a plurality of scarifiers capable of deployment and retraction during course of use of the device, as well as a landscape rake and a plurality of clod-cleaving wheels. The scarifiers can be latched in various positions depending on the user's needs. The skid steer rake can be operated in a push or pull configuration, if necessary. Another embodiment of the skid steer rake is configured to have clod-cleaving wheels adjustable to the uneven terrain while maintaining contact of the scarifiers and the skid steer rake with the ground surface.

Abstract: A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

Abstract: A manufacturing method is provided during which a preform component for a turbine engine is provided. The preform component includes a substrate and a locating feature at an exterior surface of the substrate. An outer coating is applied over the substrate. The outer coating covers the locating feature. At least a portion of the preform component and the outer coating are scanned with an imaging system to provide scan data indicative of a location of the locating feature. A cooling aperture is formed in the substrate and the outer coating based on the scan data.

Abstract: A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.

Abstract: A system for monitoring stored spent fuel rods is provided, the system comprising: canisters containing the spent fuel rods; and temperature measuring means positioned on external surfaces of the canisters. Also provided is a method for monitoring stored spent fuel rods contained in canisters, the method comprising measuring temperature of the canisters at a plurality of external surfaces of each of the canisters, recording time of temperature differences between said external surfaces, determining time of oxidation initiation of the spent fuel rods based on the recording time, and preventing oxidation from occurring.

Abstract: A manufacturing method is provided during which a preform component for a turbine engine is provided. The preform component includes a substrate. An outer coating is applied over the substrate. A characteristic of the outer coating is determined. Instructions for forming a cooling aperture are revised based on the characteristic of the outer coating to provide revised instructions. The cooling aperture is formed in the outer coating and the substrate based on the revised instructions.

Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a turbine engine component that includes a sidewall and a cooling aperture. The cooling aperture includes an inlet, an outlet, a meter section, a diffuser section and a transition section between and fluidly coupled with the meter section and the diffuser section. The cooling aperture extends through the sidewall from the inlet to the outlet. The meter section is at the inlet. The diffuser section is at the outlet. The transition section is configured to accommodate lateral misalignment between the meter section and the diffuser section.

Abstract: A system includes a tubing head spool (THS) installed in a non-plugged wellbore, the THS having a bore diameter to permit passage of one or more wellbore components corresponding to one or more wellbore components that pass through an associated blowout preventer (BOP). The system also includes an orientation sleeve arranged within the THS and installed, the orientation sleeve being positioned and aligned within the THS via one or more engagement features mating with one or more orientation features within the bore.

Abstract: A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

Abstract: A preferred embodiment is provided that utilizes psychedelics that induce the shortest possible hallucinogenic experience, to facilitate the use of fast-acting, short duration anesthetics that creates a state of unconsciousness that eliminates and/or minimizes conscious awareness and/or recall of the hallucinogenic experience. The preferred embodiment facilitates critical brain processes and activities than can potentiate the actions of psychedelics such processing supporting neurogenesis, synaptogenesis while blocking inflammatory cytokine activity particularly in the brain and potentiating the activity of anti-inflammatory cytokines.

Abstract: A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

Abstract: A manufacturing method is provided. During this method, a preform component for a turbine engine is provided that includes a substrate. A meter section of a cooling aperture is formed in the substrate. An external coating is applied over the substrate. At least a portion of the substrate and the external coating is scanned with an imaging system to provide scan data indicative of an internal structure of the portion of the substrate and the external coating. A diffuser section of the cooling aperture is formed in the external coating and the substrate based on the scan data.

Abstract: A manufacturing method is provided during which a preform component for a turbine engine is provided. The preform component includes a substrate. An outer coating is applied over the substrate. A characteristic of the outer coating is determined. Instructions for forming a cooling aperture are revised based on the characteristic of the outer coating to provide revised instructions. The cooling aperture is formed in the outer coating and the substrate based on the revised instructions.

Abstract: A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A preform meter section and a preform diffuser section are formed in the substrate. An internal coating is applied to at least the preform meter section to provide a meter section of a cooling aperture. External coating material is applied over the substrate. The applying of the external coating material forms an external coating over the substrate. The applying of the external coating also builds up the external coating material within the preform diffuser section to form a diffuser section of the cooling aperture.