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 nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component 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 leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is 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. 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: The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.

Abstract: A turbine assembly includes a rotary component rotatable about an axis of a turbine, a plurality of inner wall segments coupled to the rotary component circumferentially around the rotary component and rotatable with the rotary component, a non-rotary component circumferentially surrounding the rotary component, a plurality of outer wall segments coupled to the non-rotary component and disposed to extend toward the rotary component, and a plurality of nozzles extending from each of the outer wall segments, each nozzle having a tip distal from the outer wall segment such that the tips form a seal with the inner wall segments at an inner flow path of the turbine. An inner wall assembly and a turbine assembly method are also disclosed.

Abstract: A system may include a stone analyzer, a controller, a laser generator, and a beam combiner. The stone analyzer may be configured to generate an output relating to a natural or resonance frequency of a kidney or bladder stone. The controller may be configured to determine the natural or resonance frequency of the stone based on the output from the stone analyzer, and match a resultant pulse repetition rate with the natural or resonance frequency. The laser generator may be configured to generate at least two laser pulse trains, with each laser pulse train including laser pulses at a pulse repetition rate. The beam combiner may be configured to combine the at least two laser pulse trains into a combined laser pulse train including laser pulses at the resultant pulse repetition rate.

Abstract: A rotor blade includes a mounting portion comprising a mounting body that is formed to receive a coolant therein. An airfoil portion extends substantially radially outwardly from the mounting body and includes an airfoil body. The mounting body and the airfoil body define a plurality of primary cooling passages that extend substantially radially therein for routing the coolant through the airfoil body. Each of the primary cooling passages includes a cooling flow outlet that is formed along a tip portion of the airfoil body. The airfoil body further defines a plurality of trailing edge cooling passages, each having a coolant outlet that is formed along a trailing edge portion of the airfoil body. At least a portion of the trailing edge cooling passages are formed along a radially outer portion of the trailing edge proximate to the tip portion of the airfoil body.

Abstract: A turbine blade includes a tip shroud having a seal rail. The seal rail includes a tangential surface extending between tangential ends. The turbine blade includes a root portion configured to couple to a rotor and an airfoil portion extending between the root portion and the tip shroud. The seal rail includes a cooling passage extending along a length of the seal rail. The cooling passage is fluidly coupled to a cooling plenum to receive a cooling fluid via an intermediate cooling passage extending between the cooling passage and a cooling plenum. The seal rail includes cooling outlet passages fluidly coupled to the cooling passage. The cooling outlet passages are disposed within the seal rail and extend between the cooling passage and the tangential surface of the seal rail. The cooling outlet passages are configured to discharge the cooling fluid from the tip shroud via the tangential surface.

Abstract: A gas turbine blade may have a bond coat applied to its surface. A porous substrate may be applied to the bond layer and one or more protective layers may be applied to the bond layer such that the fiber mesh is embedded between the bond layer and the protective layer to prevent creep.

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: The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface.

Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A connection portion extends radially inwardly from the radially inner surface of the platform. An airfoil extends radially outwardly from the radially outer surface of the platform to an airfoil tip. The airfoil includes a leading edge portion and a trailing edge portion. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet defined by the connection portion to one or more outlet passages at least partially defined by the trailing edge portion of the airfoil. At least one of the one or more outlet passages include an entrance and an exit radially inwardly offset from the entrance.

Abstract: Methods and apparatus to monitor a media presentation are disclosed. An example apparatus includes a housing defining a sleeve dimensioned to receive a monitoring device, the monitoring device to monitor the media presentation. The example apparatus includes a receiver carried by the housing to receive a first modulated audio signal from a media device via a wireless data connection using a wireless communication protocol, the first modulated audio signal associated with the media presentation, the receiver to output a baseband audio signal corresponding to the first modulated audio signal. The example apparatus includes a speaker carried by the housing to emit the baseband audio signal for receipt by the monitoring device within the sleeve. The example apparatus further includes a monitoring device to be received by the housing to receive the baseband audio signal from the speaker, and to generate research data identifying the media.

Abstract: The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform comprising a radially inner surface, an undulating radially outer surface, a leading edge portion, a trailing edge portion, a pressure-side slash face, and a suction-side slash face. An airfoil extends outwardly from the undulating radially outer surface of the platform to an airfoil tip. A connection portion extends radially inwardly from the radially inner surface of the platform. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet in the connection portion through the airfoil to a plurality of outlet plena in the platform. Two or more outlet plena of the plurality of outlet plena are spaced equidistant from the undulating radially outer surface of the platform.

Abstract: A casted turbine bucket having at least one machined plenum including a plenum chamber and at least one plenum passage connected to a plenum inlet at a root portion of turbine bucket, and a method to feed cooling flow to the turbine bucket using the machined plenum that receives cooling flow from the root portion of the turbine bucket.

Abstract: A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge root extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge root. A related turbomachine is also disclosed.

Abstract: A method of forming a ceramic matrix composite component includes providing a formed ceramic member having a cavity, filling at least a portion of the cavity with a ceramic foam. The ceramic foam is deposited on a barrier layer covering at least one internal passage of the cavity. The method includes processing the formed ceramic member and ceramic foam to obtain a ceramic matrix composite component. Also provided is a method of forming a ceramic matrix composite blade and a ceramic matrix composite component.

Abstract: In one aspect of the present disclosure, an airfoil for a rotor blade of a gas turbine includes a normalized pressure side wall portion thickness, a normalized suction side wall portion thickness, a normalized leading edge wall thickness, and a normalized trailing edge wall thickness. The values of theses thicknesses define the pressure side wall portion thickness, the suction side wall portion thickness, the leading edge wall thickness, and the trailing edge wall thickness, which improve heat transfer, flow distribution, and mechanical load transfer.

Abstract: Methods and apparatus to monitor a media presentation are disclosed. An example apparatus includes a housing defining a sleeve dimensioned to receive a monitoring device, the monitoring device to monitor the media presentation. The example apparatus includes a receiver carried by the housing to receive a first modulated audio signal from a media device via a wireless data connection using a wireless communication protocol, the first modulated audio signal associated with the media presentation, the receiver to output a baseband audio signal corresponding to the first modulated audio signal. The example apparatus includes a speaker carried by the housing to emit the baseband audio signal for receipt by the monitoring device within the sleeve.

Abstract: Aspects of this disclosure pertain to a device with an elongated body having a distal end. The distal end may comprise a port that permits discharge of a laser energy towards a tissue from an optical fiber located in the distal end. An exterior surface of the distal end may include a cauterization portion that permits discharge of a cauterization energy towards the tissue. In some aspects, the device includes an insulative portion that attaches the distal end to the elongated body and limits energy transfer therebetween. Related systems and methods are also disclosed.