Abstract: An anaerobic digestion system may include a material grinding/pulping portion, a hydrolysis portion arranged downstream of the grinding portion, a multiple chamber anaerobic reactor arranged downstream from the hydrolysis portion and including a gas collection and reintroduction system, a collection system for collecting digestate and gas from the anaerobic reactor.

Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.

Abstract: The invention relates to the preparation of novel bi- or tri-metallic silicate micro-porous and/or meso-porous materials based on cerium, nickel, copper and/or zinc on a porous silicate framework matrix to use its molecular sieve effect to target preferentially the acidic organic molecules present in hydrocarbon feedstocks like crude oil, bitumen, VGO and the like. The chosen metals are selected based on their ability to activate steam and transfer oxygen for completing the oxidation of carboxylic compounds or decarboxylating them. These composite materials can be prepared under hydrothermal synthesis conditions in order to produce suitable porous solids where the metals are well dispersed and preferentially distributed inside the channels of the silicate framework where they can interact only with the molecules that can go inside the channels.

Abstract: An appliance and method of operation is provided. The appliance may include an outer casing, a user interface, and a controller. The outer casing may define an enclosed volume. The user interface may be mounted to the outer casing to include a light projector and a translucent diffuser disc. The light projector may be positioned within the enclosed volume and include a plurality of discrete segmented light emitting diodes to each selectively emit one or more discrete light emissions. The translucent diffuser disc may be positioned between the light projector and the outer casing. The diffuser disc may include a continuous outer surface aligned with the light projector to display the one or more discrete light emissions as a visually continuous pattern. The controller may be operably connected with the light projector and configured to determine the visually continuous pattern displayed at the continuous outer surface.

Abstract: A turbine airfoil for a gas turbine engine includes a pressure sidewall extending along a spanwise direction, and from a leading edge of the airfoil towards the trailing edge of the airfoil. The turbine airfoil additionally includes a suction sidewall also extending along the spanwise direction, and from the leading edge towards the trailing edge. The pressure sidewall and suction sidewall define a cooling air cavity therebetween, and one or both of the pressure sidewall and suction sidewall define a trailing edge cooling channel extending from the cooling air cavity substantially to the trailing edge. Additionally, one or both of the pressure sidewall and suction sidewall include a plurality of pressure drop members extending partially into the trailing edge cooling channel for reducing an amount of cooling air flowing therethrough from the cooling air cavity.

Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided upstream of the outlet.

Abstract: Certain aspects of the present disclosure generally relate to a touch panel. The touch panel may include a cover layer, of a plurality of layers, configured to receive a touch force applied to the touch panel. The touch panel may include a force determination set of layers, of the plurality of layers, to determine a magnitude of the touch force applied to the touch panel. The force determination set of layers may include a piezoelectric layer with a set of force determination pixels. The set of force determination pixels may be arranged in a matrix to address the set of force determination pixels. A force determination pixel may be configured to generate a charge for determining a location of the touch force applied to the touch panel and a magnitude of the touch force applied to the touch panel.

Abstract: An engine component for a gas turbine engine includes a film-cooled wall having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. A film hole in the wall has an inlet, an outlet, and a passage connecting the inlet and outlet that defines an inflection point.

Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.

Abstract: Disclosed herein is a process suitable for constructing a multiple stage air shock. The multiple stage air shock is unique among shocks in that the multiple stage design possesses qualities not available to other shock absorbers. The process includes a means for determining the compressed and extended lengths of the air shock based on the lengths of the parts for each stage. This means refers to one methodology and offers the air shock an extended length that is greater than twice its compressed length, an optimized extended length, and a construction capability based on adding stages. In particular, the extended length-compressed length relationship is a quality inherently unobtainable by current shock absorbers. The process also includes a means of determining the spring rate. This means refers to a second methodology and offers the capability to both set-up the air shock with a relatively linear spring rate and make the relatively linear spring rate more linear.

Abstract: An airfoil comprises at least one wall defining a leading edge, a trailing edge, a pressure side extending between the leading edge and the trailing edge, and a suction side extending between the leading edge and the trailing edge. The airfoil is curved in three dimensions and has one or more cavities defined by an interior surface of the at least one wall. A plurality of cooling film holes extending between the cavity and at least one cooling trench located on at least one of the pressure side and the suction side, spaced from the leading edge. The at least one trench has a floor spaced from an outer surface of the airfoil. The plurality of cooling film holes extend through the floor at an angle other than perpendicular.

Abstract: Methods, systems, and apparatus for circuit breakers with integrated safety, control, monitoring, and protection features. In one aspect, a circuit breaker includes, an input and an output, a switch coupled between the input and the output, a sensor configured to measure the current flowing from the input to the output, and a control system coupled to the sensor and the switch, wherein the control system is configured to perform operations including comparing a rate of change of the current measured by the sensor to a threshold rate of change of current, determining that the rate of change of the current measured by the sensor exceeds the threshold rate of change of current for at least a predetermined period of time, and as a consequence of determining that the rate of change of current exceeds the threshold rate of change, opening the switch, thereby disconnecting the input from the output.

Abstract: A gas turbine engine turbine blade includes internal structural support radially supporting aerodynamic fairing. Strut radially extends away from root of support. Fairing includes hollow fairing airfoil surrounding strut and extending from fairing platform to blade tip shroud at tip of the fairing airfoil. A support cap attached to radially outer end of strut outwardly restrains fairing. Seal teeth may extend outwardly from the support cap. Internal cooling air flow path may extend radially through support. Fairing may be made from material lighter in weight than the support. Fairing material may be ceramic matrix composite and support material may be metallic. Blades may be mounted in rim of disk by roots disposed in slots through rim. Annular plate mounted to, upstream of, and proximate web of disk defines in part cooling airflow path to slot.

Abstract: Reagents, methods, and kits for assaying enzymes associated with lysosomal storage diseases MPS-I, MPS-II, MPS-IIIA, MPS-IIIB, MPS-IV A, MPS-VI, and MPS VII. In one aspect, the invention provides methods for assaying one or more enzymes associated with a lysosomal storage disease. In a first embodiment, the method includes: (a) contacting a sample with a first solution to provide a solution comprising one or more lysosomal enzymes; (b) contacting the one or more lysosomal enzymes in solution with an enzyme substrate for each lysosomal enzyme to be analyzed and incubating the substrates with the enzymes for a time sufficient to provide a solution comprising an enzyme product for each lysosomal enzyme present in the sample.

Abstract: A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.

Abstract: Disclosed herein is a process suitable for constructing the multiple stage air shock. The multiple stage air shock is unique among shocks in that the multiple stage design possesses qualities not available to other shock absorbers. The process includes a means for determining the compressed and extended lengths of the air shock based on the lengths of the parts for each stage. This means refers to one methodology and offers the air shock an extended length that is greater than twice its compressed length, an optimized extended length, and a construction capability based on adding stages. In particular, the extended length-compressed length relationship is a quality inherently unobtainable by current shock absorbers. The process also includes a means of determining the spring rate. This means refers to a second methodology and offers the capability to both set-up the air shock with a relatively linear spring rate and make the relatively linear spring rate more linear.

Abstract: A stand-alone ice making appliance and method of operation is provided. The stand-alone ice making appliance may include a container defining a first storage volume for receipt of ice, a water storage volume in fluid communication with the container to receive water from the container, an ice maker, a pump, and an ultraviolet light source. The ice maker may include an auger at least partially surrounded by a casing. The casing may be in fluid communication with the water storage volume to receive water from the water storage volume. The ice maker may further include a sealed refrigeration system in thermal communication with the casing. The pump may be in fluid communication with water storage volume for actively flowing water from the water storage volume to the ice maker. The ultraviolet light source may face the water storage volume to selectively direct ultraviolet light into the water storage volume.

Abstract: Stand-alone ice making appliances are provided. An appliance includes a container defining a first storage volume for receipt of ice, a water tank defining a second storage volume for receipt of water, and a pump in fluid communication with the second storage volume. The appliance further includes an ice maker which is in fluid communication with the pump for receiving water from the pump. The appliance further includes a filter, the filter including a filter medium operable to remove contaminants from water flowing through the filter medium, the filter positioned upstream of the ice maker in a flow direction of water from the second storage volume to the ice maker.

Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided upstream of the outlet.

Abstract: An engine component for a gas turbine engine can generate a hot combustion gas flow and provide a cooling fluid flow. A wall can separate the hot combustion gas flow from the cooling fluid flow. Multiple film holes can be disposed in the wall, having an inlet adjacent the cooling fluid flow and an outlet at the hot combustion gas flow such that the cooling fluid flow can be provided to the hot combustion gas flow. The film holes further comprise inlets, such that the inlets can be arranged with the inlets having at least one of a different orientation relative to one another or are non-aligned with each other relative to the cooling fluid flow.