Abstract: An electronic gaming device that includes a display device, a memory device, and a game controller including a processor is described. The processor is configured to apply a game tier to a base game, wherein the game tier corresponds to a credit award range, and cause a base game outcome including symbols displayed on reels to be displayed. The processor is also configured to determine that the base game outcome includes a prize symbol including a first credit award within the credit award range of the game tier. The processor is further configured to apply the game tier to a feature game and cause a feature game outcome including symbols displayed on reels to be displayed. The processor is further configured to determine that the feature game outcome includes the prize symbol including a second credit award within the credit award range of the game tier.

Abstract: A method of optimizing a premix fuel nozzle for a gas turbine is provided including the step of providing a nozzle that provides, when the gas turbine is in operation, an axial flow field of an air and fuel mixture flows through the burner tube and around the nozzle tip, and at least two recirculation zones with at least two differing radial extents as part of a toroidal vortex generated on the nozzle tip to provide strong flame holding and flame propagation.

Abstract: The invention relates to a formed body for the administration to animals and to a process for the production of the formed body for the administration to animals. The formed body serves in particular for the oral administration of pharmaceutically active substances to animals. The formed body for the administration to animals comprises one or more pharmaceutically active substance, one or more flavouring agents, one or more binding agents, one or more gel-forming agents, one or more fillers, water and glycerol.

Abstract: A nozzle tip for a premix fuel nozzle includes an outer body having an outer body external face facing the downstream end of the burner tube, the outer body external face having a smaller cross-sectional area than the cross-sectional area of the burner tube; and at least one segment radiating radially outwardly toward the internal wall of the burner tube from the outer body, wherein each segment has a proximal end disposed adjacent to the outer body external face and a distal end disposed in a direction toward the burner tube, wherein each segment has a segment downstream face angled relative to the longitudinal axis of the burner tube towards the downstream end of the burner tube. When the gas turbine is in operation, an axial flow field of an air and fuel mixture flows through the burner tube and around the nozzle tip, and two or more recirculation zones of differing radial extent are generated on the nozzle tip by the segments to provide strong flame holding and flame propagation.

Abstract: A method of optimizing a premix fuel nozzle for a gas turbine is provided including the step of providing a nozzle that provides, when the gas turbine is in operation, an axial flow field of an air and fuel mixture flows through the burner tube and around the nozzle tip, and at least two recirculation zones with at least two differing radial extents as part of a toroidal vortex generated on the nozzle tip to provide strong flame holding and flame propagation.

Abstract: A nozzle tip for a premix fuel nozzle includes an outer body having an outer body external face facing the downstream end of the burner tube, the outer body external face having a smaller cross-sectional area than the cross-sectional area of the burner tube; and at least one segment radiating radially outwardly toward the internal wall of the burner tube from the outer body, wherein each segment has a proximal end disposed adjacent to the outer body external face and a distal end disposed in a direction toward the burner tube, wherein each segment has a segment downstream face angled relative to the longitudinal axis of the burner tube towards the downstream end of the burner tube. When the gas turbine is in operation, an axial flow field of an air and fuel mixture flows through the burner tube and around the nozzle tip, and two or more recirculation zones of differing radial extent are generated on the nozzle tip by the segments to provide strong flame holding and flame propagation.

Abstract: Delivery of a drug is controlled to impart a delay before release after administration by formulating the drug with a disruption agent to provide a core, and coating the core with a regulatory membrane comprising a water-soluble gel-forming polymer and a water-insoluble film-forming polymer.

Abstract: A water toy comprises an elongated buoyant body, a front attachment point, a weighted figurine, and a fin. The elongated buoyant body has a nose, a tail, a top surface, and a bottom surface. The top surface and the bottom surface meet at an outer edge. The front attachment point is disposed upon the bottom surface at the nose. The front attachment point comprises an aperture. The weighted figurine is disposed upon the top surface toward the nose. The fin extends from the bottom surface toward the tail. The water toy may comprise a rear attachment point for attaching a fish hook or lure and/or a water foil disposed upon the bottom surface at the tail.

Abstract: A water toy comprises an elongated buoyant body, a front attachment point, a weighted figurine, and a fin. The elongated buoyant body has a nose, a tail, a top surface, and a bottom surface. The top surface and the bottom surface meet at an outer edge. The front attachment point is disposed upon the bottom surface at the nose. The front attachment point comprises an aperture. The weighted figurine is disposed upon the top surface toward the nose. The fin extends from the bottom surface toward the tail. The water toy may comprise a rear attachment point for attaching a fish hook or lure and/or a water foil disposed upon the bottom surface at the tail.

Abstract: A turbine engine having a plenum for passing fluids from an outlet of a compressor to an inlet of a combustor that may increase the efficiency of the turbine engine. The turbine engine may include a combustor, a compressor positioned upstream of the combustor, a transition channel extending from the compressor to the combustor, and a shell extending between the compressor and a combustor portal and positioned around the at least one transition channel. The turbine engine may also include an axial diffusor in the shell near the at least one transition channel, wherein the axial diffusor may include a fluid flow recess in a trailing edge of the axial diffusor. The turbine engine may also include a wave protrusion extending from a surface positioned radially inward of the axial diffusor. The fluid flow recess and the wave protrusion may reduce fluid flow loss within the shell.

Abstract: An aft liner seal for a combustor for a gas turbine includes an inner shell having an inner and outer surface and central axis. The aft liner seal has an outer shell positioned over the inner shell that has an inner and outer surface and central axis coaxial with the inner shell. One of the outer surface of the inner shell or the inner surface of the outer shell has grooves angled relative to the central axis. The angled grooves and adjacent portions of the inner surface of the outer shell or the outer surface of the inner shell form cooling passages. The cooling air exits the cooling passages at an exit angle that is matched to a swirl angle of the combustor flow. Matching of the exit angle and the swirl angle minimizes shear of cooling air with respect to flow exiting the combustor liner.

Abstract: The present invention is spray system such as a nozzle array, for more effectively and efficiently delivering liquid spray to air before its intake into an engine, a power augmentation system for an engine comprising the spray system and a method for more effectively humidifying air. The system is comprised of a plurality of independently-operable nozzle stages, which divide the flow path into a plurality of subsections. A group of nozzle stages comprise a unit of the system, which is comprised of a plurality of repeating units. The units are spaced to allow air flow through. The nozzle array is configured to substantially equally humidify the air through each subsection. The design of the nozzle array achieves more uniform mixing of air and water close to the point of injection of the air and water across the entire water injection range. As such, it maximizes the time available for evaporation by the drops in air that is not oversaturated.

Abstract: A secondary nozzle is provided for a gas turbine. The secondary nozzle includes a flange and an elongated nozzle body extending from the flange. At least one premix fuel injector is spaced radially from the nozzle body and extends from the flange generally parallel to the nozzle body. At least one second nozzle tube is fluidly connected to the fuel source and spaced radially outward from the first nozzle tube with a proximal end fixed to the flange. The second nozzle tube has a distal end, spaced from the proximal end, with at least one aperture therein. A passageway extends between the proximal end and the distal end of the second nozzle tube, with the passageway fluidly connecting to the fuel source and the aperture.

Abstract: A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines a passageway therein having a first side facing the nozzle and a second side facing the combustion chamber. Compressed air is directed into an inlet in fluid communication with the first and second sides of the venturi passageway. The venturi passageway directs the compressed air from the inlet in opposite directions within the first and second sides of the passageway for cooling the venturi.

Abstract: A secondary nozzle is provided for a gas turbine. The secondary nozzle includes a flange and an elongated nozzle body extending from the flange. At least one premix fuel injector is spaced radially from the nozzle body and extends from the flange generally parallel to the nozzle body. At least one second nozzle tube is fluidly connected to the fuel source and spaced radially outward from the first nozzle tube with a proximal end fixed to the flange. The second nozzle tube has a distal end, spaced from the proximal end, with at least one aperture therein. A passageway extends between the proximal end and the distal end of the second nozzle tube, with the passageway fluidly connecting to the fuel source and the aperture.

Abstract: A combustor for a gas turbine is provided having a nozzle assembly located at one end and a combustion chamber defining a second end of the combustor. A venturi is positioned within the combustor, between the nozzle and the combustion chamber. The venturi defines an internal passageway therein having a first side facing the nozzle and a second side facing the combustion chamber. Compressed air is directed into an inlet in fluid communication with the first and second sides of the internal passageway. The internal passageway directs the compressed air from the inlet in opposite directions within the first and second sides of the internal passageway for cooling the venturi.

Abstract: A turbine engine having a plenum for passing fluids from an outlet of a compressor to an inlet of a combustor that may increase the efficiency of the turbine engine. The turbine engine may include a combustor, a compressor positioned upstream of the combustor, a transition channel extending from the compressor to the combustor, and a shell extending between the compressor and a combustor portal and positioned around the at least one transition channel. The turbine engine may also include an axial diffusor in the shell near the at least one transition channel, wherein the axial diffusor may include a fluid flow recess in a trailing edge of the axial diffusor. The turbine engine may also include a wave protrusion extending from a surface positioned radially inward of the axial diffusor. The fluid flow recess and the wave protrusion may reduce fluid flow loss within the shell.

Abstract: A fluid delivery skid with a pre-fill system for supplying fluid has one or more stages including a first valve and a second valve, each having an open and closed position. The stages have active and inactive states to provide a desired flow rate of fluid to an apparatus for distribution of the fluid. In an active state, fluid is received in the stage and pressurized with the first valve open and the second valve closed. Further, in an active state, fluid is released with the first valve closed and the second open. In an inactive state, at least the second valve is closed. A control unit is connected to a pump unit and controls operation of the pump to regulate the stages to supply pressure at a level determined to achieve the desired flow rate.

Abstract: A fluid delivery skid with a pre-fill system for supplying fluid has one or more stages including a first valve and a second valve, each having an open and closed position. The stages have active and inactive states to provide a desired flow rate of fluid to an apparatus for distribution of the fluid. In an active state, fluid is received in the stage and pressurized with the first valve open and the second valve closed. Further, in an active state, fluid is released with the first valve closed and the second open. In an inactive state, at least the second valve is closed. A control unit is connected to a pump unit and controls operation of the pump to regulate the stages to supply pressure at a level determined to achieve the desired flow rate.

Abstract: A burner (27) of a gas turbine engine (10) includes a cylindrical basket (60) comprising an air flow reversal region (86). The flow reversal region ends at an air inlet plane (84) of the basket. The burner also includes a flow conditioner (90) disposed in the flow reversal region transecting an air flow (80) flowing non-uniformly through the flow reversal region, the flow conditioner being effective to mitigate variation of the air flow entering the basket across the inlet plane.