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: 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: 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: Embodiments of a surgical laser system comprise a laser source (102), a laser fiber (104), a photodetector (106) and a controller (108). The laser source is configured to generate laser energy (1 10). The laser fiber is optically coupled to the laser source and is configured to discharge the laser energy generated by the laser source. The photodetector is configured to generate an output signal (1 12) that is indicative of an intensity level of electromagnetic energy feedback (114) that is produced in response to the discharge of the laser energy. The controller is configured to control the laser source based on the output signal.

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: 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.

Abstract: A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.

Abstract: Embodiments described herein provide techniques for forming a solder mask having a repeating pattern of features formed therein. The repeating pattern of features can be conceptually understood as a plurality of groove structures formed in the solder mask. The solder mask can be included in a semiconductor package that comprises the solder mask over a substrate and a molding compound over the solder mask that conforms to the repeating pattern of features. Several advantages are attributable to embodiments of the solder mask described herein. One advantage is that the repeating pattern of features formed in the solder mask increase the contact area between the solder mask and the molding compound. Increasing the contact area can assist with increasing adherence and conformance of the molding compound to the solder mask. This increased adherence and conformance assists with minimizing or eliminating interfacial delamination.

Abstract: Embodiments disclosed herein include electronic packages and methods of forming such electronic packages. In an embodiment, the electronic package comprises, a package substrate, a die stack on the package substrate, and a mold layer encapsulating the die stack. In an embodiment, the electronic package further comprises a bond pad having a first surface and a second surface, where the die stack is electrically coupled to the first surface of the bond pad with a wire bond, and the second surface of the bond pad is substantially coplanar with a surface of the mold layer.

Abstract: Embodiments of a surgical laser systems may include a laser source configured to generate a laser energy; a laser fiber optically coupled to the laser source to discharge laser energy; a photodetector configured to generate an output signal indicative of an intensity level of electromagnetic energy feedback produced in response to the discharge of the laser energy; and a controller configured to control the laser source based on the output signal. Embodiments of a method of controlling a surgical laser system also are disclosed, wherein laser energy is generated using a laser source and discharged through a laser fiber. Electromagnetic energy feedback produced in response to discharging the laser energy is delivered to a photodetector. An output signal from the photodetector is analyzed using a controller. The laser source is controlled in response to analyzing an output signal using the controller.

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: 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.

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 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 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: This disclosure provides components and methods for blade extensions with internal features. An airfoil extends from a root connector and includes an airfoil body defining at least one air channel enclosed within the airfoil body. The air channel extends to a build surface. An additive extension extends from the build surface of the airfoil body. The additive extension includes an additive structure extending the air channel from the build surface to an external surface of the additive extension.

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 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 includes a laser generator, a laser probe, a stone analyzer, and a controller. The laser generator is configured to generate laser energy based on laser energy settings. The laser probe is configured to discharge the laser energy. The stone analyzer has an output relating to a characteristic of a targeted stone. The controller comprises at least one processor configured to determine the laser energy settings based on the output.

Abstract: A laser fiber for use in performing a medical laser treatment includes an optical fiber and a fiber tip. The optical fiber includes a terminating end surface at a distal end. The fiber tip is positioned at the distal end of the optical fiber and includes a transmissive portion and a spacer portion. Laser energy discharged from the terminating end surface of the optical fiber is transmitted through the transmissive portion. The spacer portion defines a distal terminating end of the fiber tip that is spaced a predetermined distance from the terminating end surface of the optical fiber. The predetermined distance is set for shock wave generation for calculus destruction at the distal terminating end of the fiber tip.