Abstract: A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is within a range of 0.10 to 0.40 and is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is within a range of 1-30 lbf/in2 and is defined as the bearing spanwise force divided by the fan area. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.

Abstract: A measurement system for a gas turbine engine is provided. The measurement system comprises a sensor assembly. The measurement system also includes multiple sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted within a space defined by a circumferential track embedded within an inner diameter of a casing of the gas turbine engine without having to disassemble the casing.

Abstract: The present application relates to a method for controlling a power system connected to a power grid, including: receiving a reactive power instruction and a measured reactive power from a generator; generating a reactive power error signal based on the difference between the reactive power instruction and the measured reactive power; receiving the reactive power error signal; generating a voltage instruction based on reactive power error signal; generating a voltage droop signal based on a reference reactance and a voltage at a point of common coupling; generating a voltage error signal according to at least one of the voltage instruction or the measured terminal voltage of the generator and the voltage droop signal; and producing a reactive current instruction for the converter power path based on the voltage error signal. The present application also discloses a control system for a power system connected to a power grid and a wind farm.

Abstract: A system for enhanced power system model validation is provided. The system includes a computing device including at least one processor in communication with at least one memory device. The at least one processor is programmed to store a plurality of models for a plurality of devices and a plurality of input files associated with the plurality of models, receive, from a user, a selection of model of the plurality of models to simulate, retrieve one or more input files of the plurality of input files, perform a model validity check on the selected model, if the selected model passed the model validity check, perform a model calibration on the selected model, and if the selected model passed the model calibration, perform a post evaluation on the selected model.

Abstract: A compressor bleed apparatus includes: a compressor comprising one or more rotors mounted for rotation about a central axis and enclosed in a compressor casing; a bleed slot passing through the compressor casing; an outer wall defining, in cooperation with the compressor casing, a plenum surrounding the compressor casing; at least one offtake pipe communicating with the plenum; and wherein at least one of the plenum and the bleed slot has a non-axisymmetric structure.

Abstract: Imaging agents comprising an isolated polypeptide conjugated with a radionucleide and a chelator; wherein the isolated polypeptide binds specifically to HER2, or a variant thereof; and methods for preparing and using these imaging agents.

Abstract: A first nest structure and a second nest structure are brought into alignment. When the alignment of the first nest structure and second nest structure is obtained, the operation of at least one vacuum pump is controlled such that a bearing element is released from the first nest structure and secured in the second nest structure. Movement of the bearing element from the first nest structure to the second nest structure occurs without slippage resulting in preservation of a common frame of reference used when the bearing element is in the first nest structure and the second nest structure.

Abstract: A system for creating a braze joint within a component. The system includes an environment operable to reach a braze temperature sufficient to melt at least a portion of a braze material. The system also includes a component within the environment, the component including a base having a base surface, a recess depending from the base surface into the base to an inner edge, and a braze material within the recess and forming a cap above the base surface. The braze material fills the recess from the cap to the inner edge. The cap has an exposed braze surface. The system also includes an insulation layer that at least partially covers the exposed braze surface.

Abstract: A hot gas path component assembly includes a first component portion that includes a first set of interlocking features and a second component portion that includes a second set of interlocking features mechanically coupled to the first set of interlocking features. A fill material is disposed at an interface between at least one surface of the first set of interlocking features and at least one surface of the second set of interlocking features. The fill material is disposed during a joining process. The second component portion is joined to the first component portion via both the fill material and the first and second sets of interlocking features.

Abstract: There are provided systems and methods for prognostic analytics of an asset. For example, there is provided a system for monitoring a reliability of a component of an asset. The system includes a processor and a memory comprising instructions that, when executed by the processor, cause it to perform certain operations. These operations may include receiving input data, which can include performance data relating to the component, configuration data relating to the component, and statistical data relating to a plurality of assets. The operations can further include providing a pre-emptive recommendation for the component based on the input data.

Abstract: A method for operating a wind turbine includes determining one or more loading and travel metrics or functions thereof for one or more components of the wind turbine during operation of the wind turbine. The method also includes generating, at least in part, at least one distribution of cumulative loading data for the one or more components using the one or more loading and travel metrics during operation of the wind turbine. Further, the method includes applying a life model of the one or more components to the at least one distribution of cumulative loading data to determine an actual damage accumulation for the one or more components of the wind turbine to date. Moreover, the method includes implementing a corrective action for the wind turbine based on the damage accumulation.

Abstract: A process of modifying a passage in a component is provided. The process includes inserting a first material into the passage; blocking at least one end of the passage; inserting an elongated member into the passage through the first material; heat treating the passage, the first material, and the elongated member to form a solid interior in component; and machining through the solid interior to form a modified passage in the component.

Abstract: A stator vane is provided. The stator vane including an airfoil that has a nominal suction-side profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in Table I. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at a base of the airfoil. The Cartesian coordinate values of X, Y, and Z are non-dimensional values that are convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values are connected by smooth continuing arcs to define suction-side profile sections at each Z value. The suction-side profile sections at the Z values are joined smoothly with one another to form a complete airfoil suction-side shape.

Abstract: The subject matter of the present disclosure generally relates to techniques for neuromodulation that include applying energy (e.g., ultrasound energy) into an internal tissue to cause tissue displacement and identifying that the tissue displacement has occurred. In one embodiment, the presence of tissue displacement is associated with a desired therapeutic or physiological outcome, such as a change in a molecule of interest.

Abstract: A swirler assembly includes a swirler having a primary swirler and a secondary swirler, and a flare connected the secondary swirler, and a dome disposed radially outward of the flare. A flare oxidizer flow passage is defined by a flare outer surface and a dome inner surface, and the flare oxidizer flow passage includes a swirl inducing member therewithin that induces a swirled flow of an oxidizer passing through the flare oxidizer flow passage into a combustion chamber.

Abstract: A vibration damping system for a turbine nozzle or blade includes a body opening extending through a body of the turbine nozzle or blade between a tip end and a base end thereof. Elongated vibration damping element is disposed in the body opening and includes an elongated body having a first, free end and a second end fixed relative to one of the base end and the tip end. At least one wire mesh member surrounds the elongated body. The wire mesh member(s) frictionally engage with an inner surface of the body opening to damp vibration. A related method is also disclosed.

Abstract: A method may include receiving data associated with a part to be built by additive manufacturing using a recoater, predicting a distortion amount comprising a distance that the part is expected to distort in a vertical direction at one or more layers while the part is being built based on a simulation of the part being built, determining a likelihood of a recoater event based on the predicted distortion amount, determining a severity factor associated with the predicted distortion amount at each of the one or more layers of the part based on an orientation of the part at each of the one or more layers, and determining an adjusted likelihood of a recoater event at each of the one or more layers based on the predicted distortion amount and the determined severity factor. Apparatuses and systems are also provided for enhanced recoater event prediction for DMLM additive manufacturing.

Abstract: A system and method for creating pre-compensated parts through additive manufacturing by providing more precise compensation in part regions either through a user specified selection of the region or an automatic selection of the region. An additive manufacturing system first generates a computer-aided design (CAD) image and then measures the physical representation of the component, then determines the amount to be compensated and generates a compensation field using multi-level b-spline morphing over the entire part to create a 3-D part. Embodiments can also include automation to determine the best level to morph all the points on the entire additive manufactured part, using incremental morphs, determining the correct morphing level locally, and using weights to determine what regions receive high level morphs as they are compensated.

Abstract: A system includes a sensor comprising a sensor bonding layer disposed on a surface of the sensor, wherein the sensor bonding layer is a metallic alloy. An inlay includes a planar outer surface, wherein the inlay may be disposed on a curved surface of a structure. A structure bonding layer may be disposed on the planar outer surface of the inlay, wherein the structure bonding layer is a metallic alloy. The sensor bonding layer is coupled to the structure bonding layer via a metallic joint, and the sensor is configured to sense data of the structure through the metallic joint, the structure bonding layer, and the sensor bonding layer. The inlay comprises at least one of a modulus of elasticity, a shape, a thickness, and a size configured to reduce strain transmitted to the sensor.

Abstract: A gas turbine system includes a compressor section, a turbine section, a combustor section. The combustor section is in fluid communication with a fuel supply via a fuel supply line. The water circuit includes a first water line extending between a first feed water supply line and a return water line. The gas turbine system further includes an extraction-air line that extends between an inlet port on the compressor section and an outlet port on the turbine section. A first heat exchanger thermally couples the first water line to the extraction-air line for transferring heat from a flow of extraction-air within the extraction-air line to a flow of water within the water circuit. A second heat exchanger thermally couples the first water line to the fuel supply line for transferring heat from the flow of water within the water circuit to a flow of fuel within the fuel supply line.