Abstract: A surgical instrument having a first assembly with a first radio-opaque portion providing a profile of a first portion of an intramedullary implant or canal in a bone, and a second assembly having a second radio-opaque portion providing a profile of a second portion of the intramedullary implant or canal. The surgical instrument may also include a third radio-opaque portion providing an alignment feature to provide a fluoroscopic planar check for the surgical instrument.

Abstract: An example method includes registering, via a visualization device, a virtual model of a portion of an anatomy of an ankle of a patient to a corresponding portion of the anatomy of the ankle viewable via the visualization device, the virtual model obtained from a virtual surgical plan for an ankle arthroplasty procedure to attach a prosthetic to the anatomy. The example method also comprises displaying, via the visualization device and overlaid on the portion of the anatomy, a virtual guide that guides at least one of preparation of the anatomy for attachment of the prosthetic or attachment of the prosthetic to the anatomy.

Abstract: A gas turbine engine includes a shroud with an abradable section and a non-abradable section that cooperatively define a shroud surface. The gas turbine engine also includes a rotor that is supported for rotation within the shroud to generate an aft axial fluid flow. The rotor includes a blade with a blade tip that is crowned and that opposes the abradable section and the non-abradable section of the shroud surface. A crown area of the blade tip opposes the abradable section. A casing treatment feature is provided in the non-abradable section of the shroud to oppose the blade tip of the rotor.

Abstract: An apparatus for use in marine platform jacking is disclosed herein. In one aspect, a jetting valve includes a valve body with a piston assembly disposed therein. The piston assembly is selectively operated to open and close the valve. A biasing member is coupled to the piston assembly. The piston assembly includes a first piston and a second piston. The dual pistons, in cooperation with the biasing member, allow the valve to self-seal thereby preventing entry of a fluid which is external to the valve.

Abstract: A system includes a circuit breaker and an adapter. The circuit breaker includes a front face with a light source on the front face. The adapter is configured to be releasably held on the front face in an installed position. The adapter includes a light sensor that aligns with the light source in the installed position. The light source and the light sensor are configured to communicate such that the adapter receives operational data from the circuit breaker in the installed position.

Abstract: A gas turbine engine includes a shroud with an abradable section and a non-abradable section that cooperatively define a shroud surface. The gas turbine engine also includes a rotor that is supported for rotation within the shroud to generate an aft axial fluid flow. The rotor includes a blade with a blade tip that is crowned and that opposes the abradable section and the non-abradable section of the shroud surface. A crown area of the blade tip opposes the abradable section. A casing treatment feature is provided in the non-abradable section of the shroud to oppose the blade tip of the rotor.

Abstract: Provided herein are devices, systems, and methods for removing contaminant ions from water within an aquifer. The devices, systems, methods employ an elecrokinetic driving force to induce the migration of charged species towards electrodes, where they can be concentrated and removed from the aquifer. In this way, the devices, systems, methods described herein can be used to economically remediate groundwater contaminated with charged species.

Abstract: Rotor systems and methods for improved performance with extended range to stall fabricated through the use of additive manufacturing. A rotor has blades that extend to tips and rotates about an axis. A casing fits over the rotor so that the tips are configured to pass proximate the casing when the rotor rotates. The casing channels a flow stream across the rotor. Grooves are defined in the casing and extend longitudinally at an acute angle relative to the axis. The grooves extend a distance upstream from a leading edge of the blades and over at least a portion of the blade tips so that the blade tips are configured to pass across the grooves when the rotor rotates.

Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.

Abstract: A method for obtaining operational data from a circuit breaker includes: releasably attaching an adapter to a circuit breaker; actuating a test button on the circuit breaker using the adapter; moving a handle of the circuit breaker to an on position; initiating output of a light signal from the circuit breaker that is representative of operational data of the circuit breaker in response to the actuating and moving steps; and receiving the light signal at the adapter.

Abstract: A compressor section includes a shroud surface and a rotor with a blade tip that opposes the shroud surface. The rotor is configured to rotate within the shroud about an axis of rotation. Moreover, the compressor section includes a serration groove that is recessed into the shroud surface. The serration groove includes a forward portion with a forward transition and a forward surface that faces in the downstream direction. The forward transition is convexly contoured between the shroud surface and the forward surface. The serration groove includes a trailing portion with a taper surface and a trailing transition. The taper surface tapers inward as the taper surface extends from the forward surface to the trailing transition. The trailing transition is convexly contoured between the taper surface and the shroud surface.

Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.

Abstract: A method of manufacturing a multistage axial-centrifugal compressor for a gas turbine engine and a multistage axial-centrifugal compressor that includes a series of axial compressor stages each having a rotor mounted to a common shaft positioned upstream from a centrifugal compressor stage mounted to the common shaft. The method includes determining an operational rotor tip speed for each of the axial stages. The method includes comparing the operational rotor tip speed to a threshold range value and determining to machine an airfoil of the rotor for at least one of the axial stages by an arbitrary manufacturing approach based on the operational rotor tip speed as greater than the threshold range value. The method includes determining to machine an airfoil of the rotor for at least one of the axial stages by a flank manufacturing approach based on the operational rotor tip speed as less than the threshold range value.

Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each having a button forward edge portion and the airfoil including leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge, at least a portion of which extends forward of the buttons, includes a local aft sweep at the tip, thereby forming a locally swept tip of the leading edge thereat. The button forward edge portion of the outer button is substantially vertically aligned with the locally swept tip of the leading edge. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.

Abstract: A rotor blade comprises a mount and a blade that extends from the mount along a radial axis. The leading edge includes an indent segment. The leading edge has a leading edge radial length measured along the radial axis. The indent segment has an indent radial length measured along the radial axis. The indent segment has an indent depth. A first ratio of the indent radial length to the leading edge radial length is at most 0.5. A second ratio of the indent depth to the indent radial length is at least 0.05.

Abstract: A rotary introducer is provided for introducing a trackable element and/or contaminant onto a flow path of a food-transit system without adjusting a flowrate. The introducer comprises an inlet and an outlet which is communicable with a food-transit conduit; and a pair of rotatable driving/drivable members. In a trackable-element receiving condition, the inlet is open to receive a trackable element in the device cavity, and the outlet is closed by at least one of the driving/drivable member. However, in a discharge condition, the outlet is open such that a trackable-element discharge force is directed radially inwardly through the outlet to discharge the trackable element from the device cavity, thus enabling outlet to close. A food-transit system using the rotary introducer and a method of introducing a trackable element and/or contaminant into food-transit system without adjusting a flowrate of foodstuffs therethrough are also provided.

Abstract: A gas turbine engine includes a shroud with an abradable section and a non-abradable section that cooperatively define a shroud surface. The gas turbine engine also includes a rotor that is supported for rotation within the shroud to generate an aft axial fluid flow. The rotor includes a blade with a blade tip that is crowned and that opposes the abradable section and the non-abradable section of the shroud surface. A crown area of the blade tip opposes the abradable section. A casing treatment feature is provided in the non-abradable section of the shroud to oppose the blade tip of the rotor.

Abstract: A system and distributed computing process for facilitating personal introductions relative to a social event are disclosed. One or more users who are attending or have attended a social event indicate an interest in one or more other users for a stated purposes. Such indication may take place by interacting with a profile photograph of the other user attending or who attended the social event. Only if the distributed computing process determines that two users have expressed mutual interest in one another for a matching purpose, the distributed computing process notifies both users of their common interest in each other.

Abstract: A compressor for a turbine engine includes a shroud having a grooved section including a plurality of groove segments extending radially into a shroud surface. A rotor assembly rotatably supported in the shroud includes a rotor hub and a plurality of rotor blades. Each rotor blade extends radially from the rotor hub and terminates at a blade tip, which is spaced from the shroud surface by a tip gap and defines a non-constant clearance region between a leading edge position and a medial chord position along the blade chord at the minimum tip clearance. The rotor blades generate an aft axial fluid flow through the shroud and the grooved section is formed in the shroud surface upstream of the medial chord positon within the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap when the compressor section is operated at near stall conditions.

Abstract: A compressor for a turbine engine includes a shroud having a grooved section including a plurality of groove segments extending radially into a shroud surface. A rotor assembly rotatably supported in the shroud includes a rotor hub and a plurality of rotor blades. Each rotor blade extends radially from the rotor hub and terminates at a blade tip, which is spaced from the shroud surface by a tip gap and defines a non-constant clearance region between a leading edge position and a medial chord position along the blade chord at the minimum tip clearance. The rotor blades generate an aft axial fluid flow through the shroud and the grooved section is formed in the shroud surface upstream of the medial chord position within the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap when the compressor section is operated at near stall conditions.