Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.

Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.

Abstract: A surgical laser system includes a pump module configured to produce pump energy within an operating wavelength, a gain medium configured to convert the pump energy into first laser energy, a non-linear crystal (NLC) configured to convert a portion of the first laser energy into second laser energy, which is a harmonic of the first laser energy, an output, and a first path diversion assembly having first and second operating modes. When the first path diversion assembly is in the first operating mode, the first laser energy is directed along the output path to the output, and the second laser energy is diverted from the output path and the output. When the first path diversion assembly is in the second operating mode, the second laser energy is directed along the output path to the output, and the first laser energy is diverted from the output path and the output.

Abstract: A surgical laser system (100) includes a first laser source (140A), a second laser source (140B), a beam combiner (142) and a laser probe (108). The first laser source is configured to output a first laser pulse train (144, 104A) comprising first laser pulses (146). The second laser source is configured to output a second laser pulse train (148, 104B) comprising second laser pulses (150). The beam combiner is configured to combine the first and second laser pulse trains and output a combined laser pulse train (152, 104) comprising the first and second laser pulses. The laser probe is optically coupled to an output of the beam combiner and is configured to discharge the combined laser pulse train. In some embodiments, a surgical laser system includes a laser generator (102), a laser probe (108), a stone analyzer (170), and a controller (122). The laser generator is configured to generate laser energy (104) based on laser energy settings (126). The laser probe is configured to discharge the laser energy.

Abstract: A surgical laser system includes an array of laser diodes that are configured to output laser energy, a fiber bundle, a delivery fiber, and a tubular sheath. The fiber bundle includes a plurality of optical fibers and has a proximal end that is configured to receive laser energy from the array of laser diodes. The delivery fiber includes a proximal end that is configured to receive laser energy from a distal end of the fiber bundle. The tubular sheath defines a lumen, in which at least a portion of the delivery fiber is disposed. The tubular sheath is insertable into a working channel of an endoscope or a cystoscope. A distal end of the tubular sheath is configured to deliver laser energy discharged from the delivery fiber into a body of a patient.

Abstract: A coating is applied to a base material. The coating comprises a viscoelastic layer having a surface in which cavities are formed; and a constraint layer. The viscoelastic layer is disposed on the base material, and the constraint layer is disposed on, and partially bonded, at an interface, to the viscoelastic layer over the surface in which the cavities are formed. The cavities are filled with particles configured for vibration and frictional interaction at the partially bonded interface between the partially bonded viscoelastic layer and the constraint layer. A turbine blade having an airfoil with the subject coating is also provided.

Abstract: Example client management systems and methods are described. In one implementation, a client management system identifies a client of a trainer and determines a scheduling rule associated with the client. The scheduling rule defines a regular schedule for the client's training sessions with the trainer. The client management system receives, from the client, a request to cancel a training session scheduled with the trainer. The client management system reschedules the training session by canceling the training session and scheduling a new training session based on the scheduling rule.

Abstract: A surgical laser system includes a first laser source, a second laser source, a beam combiner and a laser probe. The first laser source is configured to output a first laser pulse train comprising first laser pulses. The second laser source is configured to output a second laser pulse train comprising second laser pulses. The beam combiner is configured to combine the first and second laser pulse trains and output a combined laser pulse train comprising the first and second laser pulses. The laser probe is optically coupled to an output of the beam combiner and is configured to discharge the combined laser pulse train.

Abstract: A surgical laser system includes an array of laser diodes that are configured to output laser energy, a fiber bundle, a delivery fiber, and a tubular sheath. The fiber bundle includes a plurality of optical fibers and has a proximal end that is configured to receive laser energy from the array of laser diodes. The delivery fiber includes a proximal end that is configured to receive laser energy from a distal end of the fiber bundle. The tubular sheath defines a lumen, in which at least a portion of the delivery fiber is disposed. The tubular sheath is insertable into a working channel of an endoscope or a cystoscope. A distal end of the tubular sheath is configured to deliver laser energy discharged from the delivery fiber into a body of a patient.

Abstract: A coating is applied to a base material. The coating comprises a viscoelastic layer; and a constraint layer; wherein the viscoelastic layer is disposed on the base material and the constraint layer is disposed on the viscoelastic layer.

Abstract: An article, such as a turbine blade, includes an airfoil. The airfoil includes a body, the body having an elongated internal cavity extending from a tip of the body. The cavity is defined an internal wall within the body. At least one elongated damping element is disposed in the elongated internal cavity and frictionally engages the internal wall. Thus, the least one elongated damping element is capable of damping vibrations in the article.

Abstract: A turbine blade includes an airfoil body having an outer tip and a platform; and a part-span shroud positioned between the outer tip and the platform of the airfoil body. The part-span shroud has a first opening extending through the airfoil body and having a first inner surface. The airfoil body includes a second opening extending radially from the first opening and having a second inner surface. A first elongated vibration-damping element is disposed in the first opening, and a second elongated vibration-damping element disposed radially in the second opening. The second elongated vibration-damping element includes a free radially outer end and a radially inner end coupled to the first elongated vibration-damping element. The first elongated vibration-damping element frictionally damps vibration, and the second elongated vibration-damping element damps vibration using impact within the second opening.

Abstract: Techniques are provided for controlling an output laser pulse signal of a medical device. A control device defines a time duration of capacitive discharge to a laser device. The time duration corresponds to an intended energy of the output laser pulse signal. The control device generates a plurality of sub-pulse control signals. The sub-pulse control signals define a series of capacitive discharge events of the capacitor bank. The control device modulates one or more of a sub-pulse control signal period or a sub-pulse time duration of the sub-pulse control signals to modify the capacitive discharge of the capacitor bank to the laser device during the time duration.

Abstract: Methods and apparatus to monitor a media presentation are disclosed. An example system includes a monitoring device to monitor a media presentation and generate research data identifying the media. A bridge device includes a housing dimensioned to receive the monitoring device, a receiver carried by the housing to receive a first audio signal via a wireless data connection from an audio source device using a wireless communication protocol, the first audio signal associated with the media. The bridge device includes an audio emitter to emit the audio signal for receipt by the monitoring device, and a transmitter to transmit the audio signal to an audio receiver device using the wireless communication protocol.

Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.

Abstract: Embodiments described herein provide a semiconductor package comprising multiple dies encapsulated in multiple molding compounds. In one example, a semiconductor package comprises: a first die or die stack on a substrate; a first molding compound encapsulating the first die or die stack on the substrate; a second die or die stack on the first molding compound; and a second molding compound encapsulating the second die or die stack and at least one portion of the first molding compound. In this example, the first die or die stack is electrically coupled to the substrate using a first wire bond and the second die or die stack is electrically coupled to the substrate using a second wire bond. Additionally, the first molding compound encapsulates the first wire bond and the second molding compound encapsulates the second wire bond. Furthermore, a footprint of the second die overlaps a footprint of the first die.

Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil is defined between a pressure face and a laterally opposed suction face, the pressure face and the suction face extending axially between opposite leading and trailing edges and radially between an outboard tip and a connection with a root of the rotor blade. The airfoil may include non-integral portions in which: a base portion of the airfoil is made from a first material; and a top portion of the airfoil is made from a second material. The airfoil may include a dovetail joint connecting the top portion to the base portion. The dovetail joint may include a dovetail extending from the top portion being received within a complementary dovetail groove formed in the base portion.

Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral portions in which: a base portion is made from a first material; and a top portion is made from a second material. The airfoil may include a connector securing the base portion to the top portion of the airfoil, wherein the connector comprises a wire-lock connector that includes: a tab extending from one of the base portion and the top portion; a complimentary slot for receiving the tab formed in the other one of the base portion and the top portion; a first groove formed in a side of the tab; a second groove formed in a side of the slot; a retaining aperture formed cooperatively via an alignment of the first and second grooves upon the tab being received into the slot; and a retaining wire housed within the retaining aperture.

Abstract: Methods and apparatus to monitor a media presentation are disclosed. An example system includes a monitoring device to monitor a media presentation and generate research data identifying the media. A bridge device includes a housing dimensioned to receive the monitoring device, a receiver carried by the housing to receive a first audio signal via a wireless data connection from an audio source device using a wireless communication protocol, the first audio signal associated with the media. The bridge device includes an audio emitter to emit the audio signal for receipt by the monitoring device, and a transmitter to transmit the audio signal to an audio receiver device using the wireless communication protocol.

Abstract: A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.