Abstract: A system for protecting a transformer is provided. The system includes an inductor electrically disposed between the transformer and a load powered by the transformer, and a resistor electrically disposed in parallel with the inductor between the transformer and the load.

Abstract: A system for compensating for a back emission current in an X-ray generator is provided. The system includes a transformer, a common, and a voltage source. The transformer is operative to provide power to an electron emitter of the X-ray generator. The common is electrically coupled to an anode of the X-ray generator. The anode is operative to receive electrons emitted by the electron emitter such that the back emission current is generated between the common and the electron emitter. The voltage source electrically couples the common to the transformer and is operative to generate an offset voltage that reduces the back emission current.

Abstract: A method of controlling a ventilator to provide spontaneous breathing support includes determining a target CO2 value, determining a support pressure, detecting a patient-generated spontaneous breath, and delivering ventilation gas to the patient based on the support pressure. A patient CO2 is then measured, along with measuring at least one of a patient breath rate and a breath volume. The patient CO2 is compared to the target CO2 value. The patient's respiratory drive is determined based on at least one of the patient breath rate and the breath volume. If elevated respiratory drive is detected, then the support pressure is adjusted accordingly. If elevated respiratory drive is not detected, then the target CO2 value is adjusted based on the measured patient CO2.

Abstract: An inertial separator for removing particles from a fluid stream includes a body defining a through passage, with at least one separator inlet and at least one separator outlet, a turn provided in the body between the at least one separator inlet and the at least one separator outlet, and a flow splitter having at least one particle outlet fluidly coupled to the outside of the through passage.

Abstract: A system including a quench system that may cool a syngas generated in a gasification chamber. The quench system includes a quench chamber, a dip tube that may direct the syngas from the gasification chamber into a quench liquid in the quench chamber to cool the syngas and to generate a first cooled syngas, and a draft tube disposed circumferentially about the dip tube and configured to receive the first cooled syngas in a first direction along a first passage. The first passage is disposed between a first wall of the dip tube and a second wall of the draft tube. The quench system also includes a droplet tube that may receive the first cooled syngas from the first passage. The droplet tube includes a third wall that may redirect a flow of the first cooled syngas in a second direction different from the first direction.

Abstract: A mold assembly for use in forming a component having an outer wall of a predetermined thickness includes a mold and a jacketed core. The jacketed core includes a jacket that includes a first jacket outer wall coupled against an interior wall of the mold, a second jacket outer wall positioned interiorly from the first jacket outer wall, and at least one jacketed cavity defined therebetween. The at least one jacketed cavity is configured to receive a molten component material therein. The jacketed core also includes a core positioned interiorly from the second jacket outer wall. The core includes a perimeter coupled against the second jacket outer wall. The jacket separates the perimeter from the interior wall by the predetermined thickness, such that the outer wall is formable between the perimeter and the interior wall.

Abstract: A system for preparing a coal water slurry, comprising: a first unit for providing a stream of coarse coal water slurry; a second unit for providing a stream of fine coal water slurry; a concentration unit for receiving a portion of at least one of the stream of coarse coal water slurry and the stream of fine coal water slurry, and, providing a concentrated stream having a higher coal concentration than the portion of at least one of the stream of coarse coal water slurry and the stream of fine coal water slurry; and a mixing unit for mixing the concentrated stream and the remaining portions of the stream of coarse coal water slurry and the stream of fine coal water slurry. An associated method is also presented.

Abstract: Various embodiments include a build plate for additive manufacturing, along with a related system. The build plate may include: a first build surface having at least one recess therein; and at least one block configured to matingly engage with, and disengage with, the at least one recess, the block including a second build surface.

Abstract: A rotor blade for a gas turbine configured for use within a row of samely configured rotor blades. The rotor blade may further include: an airfoil defined between pressure and suction faces; and a midspan shroud comprising a pressure wing and a suction wing extending from the airfoil. The pressure wing and the suction wing of the midspan shroud may be configured so to cooperatively form an interface between installed neighboring ones of the rotor blades within the row of samely configured rotor blades. One of the pressure wing and the suction wing may be designated a first wing, and the first wing may include a chamber hollowed through a first surface of the first wing. The first surface of the first wing may include one of: a circumferential face formed at a distal end of the first wing; and a contact face of the first wing.

Abstract: An additive manufacturing system including a consolidation device, a build platform, an optical detector, and a controller is provided. The consolidation device is configured to form a build layer of a component. The build platform is configured to rotate about a build platform rotation axis extending along a first direction. The optical detector is configured to detect locations of at least two alignment marks. The controller is configured to receive locations of the at least two alignment marks from the optical detector. The controller is also configured to determine the locations of the build platform rotation axis and a build platform rotation center point based on a comparison between the at least two alignment marks, wherein the build platform rotation center point lies along the build platform rotation axis. The controller is further configured to control the consolidation device to consolidate a plurality of particles on the build platform.

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: An in-line propeller gearbox of a turboprop gas turbine engine includes an epicyclic gearing arrangement that has a sun gear, a ring gear and at least one planet gear disposed between and meshing with both the sun gear and the ring gear. The propeller gearbox includes a disk brake that can be operated to slow down or stop altogether the rotation of the propeller. The disk brake has an axially extending shaft having at one end a disk and at the opposite end a gear having teeth that engage with one of the gears in the epicyclic gearing arrangement. The disk brake includes a hydraulic caliper or an electric caliper that can be actuated to slow down rotation of the disk to an eventual full stop and to hold the disk at full stop to thereby stop rotation of the propeller.

Abstract: A variable stator vane includes airfoil mounted to a button centered about a rotational axis and having cylindrical portion supporting airfoil and a button undercut extending away from cylindrical portion and radially inwardly from circumference of cylindrical portion. Conical portion of button circumscribed about conical axis of revolution extends away from cylindrical portion. Conical axis of revolution may be tilted with respect to and may intersect rotational axis. Airfoil may include airfoil overhang extending radially outwardly beyond circular trailing edge of button. Variable stator vane may include airfoil disposed between spaced apart outer and inner buttons centered about a rotational axis, inner button having a cylindrical portion supporting airfoil and circumscribed about rotational axis, and button undercut extending away from cylindrical portion and radially inwardly from a circumference of cylindrical portion with respect to rotational axis.

Abstract: The present approach relates to the design and use of a functionally closed bioreactor designed to immobilize, culture, and mature tissue on a loading platform. The bioreactor may be equipped with sensors for tissue monitoring which in conjunction with stiffness data can provide closed-loop control of tissue maturation. Based on a relationship between cartilage stiffness and tissue maturity, measurements of stiffness can be acquired and used as a surrogate for cartilage maturity without the need for destructive tests.

Abstract: A system and method are provided for displaying information related to a medical imaging scan. Visual regions are shown on a display screen to indicate information of pending, current, and completed medical imaging scans. If additional correction time was utilized for particular table positions in a medical imaging scan, this information is shown on the display screen, in the form of icons, shading, or other visual representations. The medical imaging system may include positron emission tomography (PET) and single photon emission computed tomography (SPECT).

Abstract: Various embodiments include a steam turbine drum nozzle, along with a related assembly and steam turbine. Particular embodiments include a nozzle having: an airfoil; a radially inner sidewall coupled with a first end of the airfoil; and a radially outer sidewall coupled with a second end of the airfoil, the second end opposing the first end, wherein the radially outer sidewall includes: a first section radially outward of the airfoil; a thinned section coupled with the first section; and a second section coupled with the thinned section radially outward of the airfoil, the second section having a radially outer face and a circumferentially facing side abutting the radially outer face, wherein the second section includes a circumferentially extending slot, and wherein the second section includes a relief slot extending into a body of the second section from the circumferentially facing side.

Abstract: An air-shielded fuel injection assembly for use in a combustion chamber of a turbine assembly. The air-shielded fuel injection assembly generally includes a fuel manifold including a plurality of fuel injection ports and an air manifold including a plurality of air injection ports. Each of the plurality of fuel injection ports is configured to introduce a fuel column into an annular cavity of a mixer assembly. Each of the plurality of air injection ports is configured to introduce an air curtain about an associated fuel injection column to minimize recirculation upstream of the fuel injection column and increase penetration of the fuel injection column into the cavity. Also disclosed are a mixer assembly and a turbine assembly including the air-shielded fuel injection assembly.

Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: A method for controlling and enhancing a startup operation for a combined cycle power block (block) having at least one gas turbine and at least one steam turbine, wherein operating parameters define performance and operational characteristics for the startup operation, the method comprising: receiving measured operating parameters from a plurality of reference blocks and, for each of the plurality of reference blocks, a plurality of types of the startup operations; given the measured operating parameters, developing one or more reference transfer functions between two of the measured operating parameters; receiving measured operating parameters from the startup operation of a target block; given the measured operating parameters from the target block, developing one or more transfer functions for the target block between two of the operating parameters; selecting one of the reference transfer functions; and normalizing the transfer function of the target block per the selected reference transfer function.