Abstract: This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. In some examples, seal assembly includes an oleophilic coating disposed between the stationary and rotating components. The seal assembly may include a surface texture to enhance the oleophilicity of the surface coating disposed between the stationary and rotating components. In other examples, the seal assembly includes an oleophobic coating disposed between the stationary and rotating components. The seal assembly may include a surface texture to enhance the oleophobicity of the surface coating. During operation, the oleophilic seal assembly features retain lubricant between the stationary and rotating components and the oleophobic seal assembly features inhibit the escape of lubricant from the contact regions between the stationary and rotating components.

Abstract: The present discussion relates to structures and devices to facilitate application of an ultrasound therapy beam to a target anatomic region in a replicable manner. In certain aspects, adjustable positioning structures are described that allow a general probe positioning structure to be configured for a specific patient in a manner that allows the device to be used repeatedly to target the anatomic region, even when in non-clinical settings. In other aspects, a probe positioning structure is fabricated that is specific to a respective patient anatomy, such that use of the probe positioning structure provides repeatable targeting of the target anatomic region, even when in non-clinical settings.

Abstract: Methods, apparatus, systems, and articles of manufacture are to control air flow separation of an engine. An example turbofan includes a nacelle having an outer lip surface, an inner lip surface, a first opening and a second opening, the first opening coupled to a first region forward of a fan of the turbofan, the second opening coupled to a second region aft of the fan, the nacelle including a first pressure sensor coupled to the outer lip surface, a second pressure sensor coupled to the inner lip surface, and an actuator, and a conduit coupled to the actuator, the conduit configured to have a first end and a second end, the first end coupled to the first opening, the second end coupled to the second opening.

Abstract: A fluid mixing apparatus includes mixing conduits that extend through a fluid plenum and that define injection holes therethrough. The fluid plenum, which surrounds a first wall defining a main passage fluidly coupled to a low-pressure fluid source, is surrounded itself by a second wall defining a high-pressure plenum fluidly coupled to a high-pressure fluid source. The mixing conduits fluidly couple the high-pressure plenum to the main passage, and the fluid from the fluid plenum is delivered with the high-pressure fluid to the main passage, where the fluids mix before being discharged from an outlet of the main passage. The fluid mixing apparatus may be used to mix one or more fuels with high- and low-pressure air in a gas turbine combustor. Alternately, the fluid mixing apparatus may mix a fluid with high- and low-pressure water streams.

Abstract: A multi-switch types hybrid power electronics build block (MST HPEBB) least replaceable unit converter employs a first low voltage side (for example, 1000 volt power switches) and a second high voltage side (for example, 3000 volt power switches). The MST HPEBB LRU employs multiple bridge converters connected in series and/or in parallel, and coupled in part by a 1:1 transformer. To reduce weight and volume requirements compared to known PEBB LRUs, different power switch types are employed in different bridge converters. For example, in one exemplary embodiment, low voltage 1.7 kVolt SiC MOSFETS may be employed on the lower voltage side, while at least some 4.5 kVolt Silicon IGBTs may be employed on the high voltage side.

Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can have a combustor with a combustor liner at least partially defining a combustion chamber, as well as a fuel-air mixer including at least one set of mixing tubes.

Abstract: A check valve assembly includes a first flapper, a second flapper, an internal passage formed by the first flapper and the second flapper, and a nozzle disposed within the internal passage and configured to generate an internal flow in the internal passage. In response to a fluid flow through the check valve assembly, the first flapper and the second flapper are configured to move between an open position allowing the internal flow through the internal passage and an outer flow outside the internal passage, and a closed position preventing flow through the internal passage. When the first flapper and the second flapper are operably in the open position, the internal flow has a lower pressure than the outer flow outside of the internal passage, such that the first flapper and the second flapper are maintained in the open position.

Abstract: An additive manufacturing apparatus includes a stage configured to hold a component. A radiant energy device is operable to generate and project radiant energy in a patterned image. An actuator is configured to change a relative position of the stage relative to the radiant energy device. A resin management system includes a material deposition assembly upstream configured to deposit a resin on a resin support. The material deposition assembly includes a reservoir configured to retain a first volume of the resin and define a thickness of the resin on the resin support as the resin support is translated in an X-axis direction. The material deposition assembly further includes a vessel positioned above the reservoir in a Z-axis direction and configured to store a second volume of the resin. In addition, the material deposition assembly includes a conduit configured to direct the resin from the vessel to the reservoir.

Abstract: The present disclosure relates to a medical imaging system having an X-ray source, a detector and a processing system. The the X-ray source is collimated to produce a diverging beam of radiation and transmits X-rays through an object. The detector includes detector pixels arranged in at least one row and is operative to receive the X-ray energy of the X-rays after having passed through the object. The processing system is programmed to select an initial height of the object with respect to the X-ray source plane and determine an initial time delayed summation (TDS) shift frequency based on the initial height. The processing system performs a first scan of the object based on the TDS shift frequency and determines a new height of the object based on a beam angle and an overlap of adjacent images. A new TDS shift frequency is determined based on the new height of the object if the initial height and the new height are not substantially same.

Abstract: Method, and corresponding system, for receiving and adaptively compressing sensor data for an operating manufacturing machine. The method includes determining the sensor data values at the working tool positions based on a time correlation of the values of the sensor data relative to time and the working tool positions relative to time. Tool control magnitude values relative to the working tool positions are determined based on the process data. The method further includes determining a magnitude differential, relative to the working tool positions, between the sensor data values and the tool control magnitude values. Scoring data is determined by applying a scoring function to the magnitude differential. The magnitude differential data is compressed based at least in part on the scoring data. The method further includes decompressing the magnitude differential data and determining the sensor data values versus the working tool positions based on the magnitude differential data.

Abstract: A manually operable valve for restricting airflow to and/or from a patient. The valve includes a body having one or more walls that extend between a first end and a second end. The one or more walls form a passage between the first end and the second end of the body. Two moveable members are positioned on opposing sides of the passage and axially fixed between the first end and the second end of the body. The two moveable members are configured such that depressing the two moveable members inwardly deforms the one or more walls to thereby restrict the passage. When the two moveable members are subsequently released, the one or more walls return to unrestrict the passage.

Abstract: In one aspect, the present disclosure is directed a gas turbine engine including a compressor, a combustor, and a turbine in a serial flow arrangement. The compressor includes a casing having an inner wall and an outer wall. The inner wall defines a passageway for airflow through the compressor. The casing defines a bleed cavity between the inner wall and the outer wall. The inner wall has an opening. The casing defining a channel between the opening and the bleed cavity to direct airflow into the bleed cavity. The channel is defined by a first wall and a second wall of the casing. The second wall being downstream of the first wall. A surface of the first wall has a pattern to reduce flow separation in the channel.

Abstract: A heat engine including a liner extended along a first dimension and a second dimension, wherein the liner includes a plurality of cavities formed by a honeycomb structure. Each cavity forms a volume extended from an opening at a fluid contact side of the liner and along a third dimension substantially orthogonal to the first dimension and the second dimension. The opening at the fluid contact side includes a cross sectional area of each respective volume of the plurality of cavities. The plurality of cavities is non-uniform with respect to the cross sectional area at the opening along the first dimension, the second dimension, or both.

Abstract: A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.

Abstract: A system includes a retention system configured to support a heat exchanger along a flow path within a duct. The retention system includes a first sleeve configured to extend between opposite first and second walls of the duct, a first cable extending through the first sleeve, and a first bumper coupled to the first sleeve. The first bumper is configured to contact the heat exchanger. The retention system includes a first tensioner coupled to the first cable, wherein the first tensioner is configured to provide a first tension in the first cable. The first tension is adjustable to detune the natural frequency of the heat exchanger away from any excitation load frequencies caused by an exhaust gas flow through the duct.

Abstract: Image reconstruction systems and methods include providing sensitivity maps for coils of a magnetic resonance imaging (MRI) system to a neural network. The systems and methods also include providing interleaved k-space data to the neural network, wherein the interleaved k-space data includes partial k-space data interleaved with zeros, or synthesized k-space data, to provide an extended field of view (FOV) different from a FOV utilized during acquisition of the partial k-space data, wherein the partial k-space data were obtained during a scan of a region of interest with the MRI system. The systems and methods further include outputting, from the neural network, a final reconstructed MR image based at least on the sensitivity maps and the interleaved k-space data, wherein the final reconstructed MR image includes the FOV utilized during the acquisition of the partial k-space data.

Abstract: An epicyclic gearbox is configured to transfer rotational motion between a first rotating component and a second rotating component of the gas turbine engine. The gearbox includes a centrally located sun gear, two or more planet gears circumscribing the sun gear, and a ring gear circumscribing the plurality of planet gears. The gearbox is configured such that the sun gear is drivingly coupled to the first rotating component, such that rotation of the sun gear causes rotation of each planet gear, and such that the ring gear rotates relative to the plurality of planet gears. The gearbox includes one or more shape memory alloy dampers provided in association with the sun gear, the ring gear, and/or the plurality of planet gears. The shape memory alloy damper(s) is configured in order to reduce vibrations transferred through the epicyclic gearbox to the frame, the first rotating component, and/or the second rotating component.

Abstract: A combustor for a gas turbine includes a ceramic matrix composite (CMC) dome with a swirler mounting wall formed integral with the CMC dome, and a swirler assembly including a plurality of clevis dome attachment members for connecting the swirler assembly to the CMC dome. Bushings are arranged within a plurality of dome-side swirler assembly mounting openings of the swirler mounting wall, and the CMC dome is arranged within respective ones of the plurality of clevis dome attachment members of the swirler assembly. A swirler-dome connecting member is disposed through each of the clevis dome attachment members so as to mount the swirler assembly to the CMC dome.

Abstract: Mitigating particulate intrusion to an air intake system of a gas turbine system with intrusion protective coatings tailored to locale of operation. A particulate intrusion protective coating is applied to a surface of a component of the air intake system to mitigate ingress of particulates within the air intake system and the gas turbine system. The particulate intrusion protective coating includes one or more particulate ingress influencing properties tailored to the common attributes of the particulates associated with the locale of operation of the gas turbine engine and the air intake system. The particulate ingress influencing properties affect rebounding and coalescing characteristics of the particulates at a point of impact with the applied surface having the particulate intrusion protective coating, entraining the particulates at the point of impact and inhibiting further ingress along an inlet air flow path of the air intake system into the gas turbine engine.

Abstract: The present disclosure relates to a method of fabricating a ceramic composite components. The method may include providing at least a first layer of reinforcing fiber material which may be a pre-impregnated fiber. An additively manufactured component may be provided on or near the first layer. A second layer of reinforcing fiber, which may be a pre-impregnated fiber may be formed on top the additively manufactured component. A precursor is densified to consolidates at least the first and second layer into a densified composite, wherein the additively manufactured material defines at least one cooling passage in the densified composite component.

Abstract: An airfoil component for attaching to a cropped airfoil is provided. The cropped airfoil comprises a cropped airfoil attachment section and a cropped first side opposite a cropped second side, which each extend axially between a cropped first edge and a cropped second edge to define a cropped chord length. The airfoil component comprises a body having a component first side opposite a component second side. The body defines an attachment section for attaching the airfoil component to the cropped airfoil at the cropped airfoil attachment section. The attachment section extends axially between a component first edge and a component second edge to define a component chord length, and the attachment section is oversized with respect to the cropped airfoil attachment section such that the component chord length is longer than the cropped chord length. Systems and methods also are provided.

Abstract: Some embodiments provide a system to facilitate transaction processing associated with an industrial asset supply chain having a first entity and a second entity. A first entity computer processor may retrieve, from a first entity database, information associated with pre-delivery data about the industrial asset. The first entity computer processor may then record pre-delivery data about the industrial asset via a secure, distributed transaction ledger. A second entity computer processor may retrieve, from a second entity database, information associated with a post-delivery event involving the industrial asset. The second entity computer processor may then record post-delivery event data about the industrial asset via a secure, distributed transaction ledger. The post-delivery event data might indicate, for example, that the industrial asset has been delivered, has been installed, is working properly, has been used, etc.

Abstract: A power converter apparatus comprises a set of switching elements communicatively coupled with a set of gate drive circuits. Each gate drive circuit is configured to provide a respective drive signal to a corresponding switching element, each switching element being switchably responsive to the respective drive signal. The apparatus includes a controller module configured to control an output state of the power converter, and selectively change one of a respective gate resistance and a respective gate current of a corresponding subset of the gate drive circuits based on the output state of the power converter.

Abstract: A rotor blade includes a first blade segment and a second blade segment extending in opposite directions from a chord-wise joint. Each of the first and second blade segments has at least one shell member defining an airfoil surface. The first blade segment includes a beam structure having a receiving end with at least one span-wise extending pin extending therefrom. The second blade segment includes a receiving section that receives the beam structure. The receiving section includes a chord-wise member having a pin joint slot defined therethrough. The pin joint slot receives the span-wise extending pin at the receiving end of the beam structure so as to secure the first and second blade segments together. Moreover, the chord-wise member, the pin joint slot, and/or the span-wise extending pin includes at least one compliant structure formed of a compliant material that allows a deformation thereof to follow a shear deformation of the rotor blade.

Abstract: At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a clock mounting location of the turbine component in a turbine.

Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.

Abstract: An adaptive trapped vortex combustor for a gas turbine engine includes a combustion chamber, a fuel injector, and one or more chutes. The combustion chamber is defined by an outer liner, an inner liner, and a dome, and includes a primary combustion zone within the combustion chamber defining a vortex cavity for a trapped vortex, the vortex cavity having a volume therein, a secondary combustion zone within the combustion chamber, and an opening from the primary combustion zone to the secondary combustion zone. The fuel injector injects a fuel into the primary combustion zone. The one or more chutes provide an air flow to the primary combustion zone and/or the secondary combustion zone. A feature of the adaptive trapped vortex combustor is controllable such that a residence time of the fuel in the vortex cavity is controllable based on an operating condition of the gas turbine engine.

Abstract: Provided is a synchronous electrical machine that includes a stator and a wounded rotor, the stator having a plurality of phases, each phase comprising coils connected together and magnetic stator poles cores fixed on a stator frame and evenly distributed along a stator diameter, each coil being wounded around a different magnetic stator pole core to form a magnetic stator pole, each phase comprising a same number of magnetic stator poles, the magnetic stator poles of each phase being disposed in the stator frame to form a concentric winding stator. The rotor includes a plurality of magnetic rotor pole cores evenly distributed around the rotor and rotor coils, each rotor coil being wounded around a different magnetic rotor pole core to form a magnetic rotor pole.

Abstract: A device and/or methodology are described that include a mechanism for separating erythrocytes from other constituents of blood and for purifying leukocytes from blood. The separation and purification aspects may be provided in separate components or within the same component. The separation aspect assists in separating erythrocytes (red blood cells) from other cells in blood, such as by aggregation of the red blood cells. A suitable aggregation device or device component uses chambers with at least one small dimension (e.g., a microfluidic chip) to control the interaction of the blood with a solution containing a high molecular weight polymer (e.g., dextran) to achieve separation.

Abstract: The present disclosure relates to an MRI system and a method and device for determining a waveform of oblique scanning. Specifically, provided are a magnetic resonance imaging system, a method and device for determining a gradient waveform of oblique scanning, and a computer-readable storage medium.

Abstract: A DC charging circuit for an electric vehicle includes a neutral-point clamped (NPC) rectifier and a DC/DC buck converter. The NPC rectifier is configured to convert three-phase AC power to a first DC voltage at a rectifier output stage. The DC/DC buck converter includes a first DC stage coupled to the rectifier output stage, and a second DC stage configured to be coupled to the electric vehicle. The DC/DC buck converter is configured to convert the first DC voltage to a second DC voltage to be supplied to the electric vehicle.

Abstract: A turbine engine comprising an engine core having at least a compressor section, a combustor section, and a turbine section in axial flow arrangement defining an axial direction and an engine centerline. The turbine engine further having a rotor and a stator, a carriage assembly carried by the stator, and a seal assembly biased toward the rotor.

Abstract: Systems and methods for data acquisition utilizing spare or unused databus capacity are provided. In one example aspect, the system includes a vehicle that includes an engine and a controller. The controller generates a data file indicative of Continuous Engine Operation Data (CEOD). The data file is transmitted over a serial databus to a bus recorder. Particularly, the data file is continuously generated by the controller and stored in a buffer. The available bandwidth of a transmission frame for the serial databus is determined. A portion of the data file is retrieved from the buffer based at least in part on the determined bandwidth. The portion of the data file is divided into relatively small transmission payloads and packed into the available bandwidth of the transmission frame. This process is repeated on a continuous basis and the bus recorder records the data. The data file is then reconstituted and decoded.

Abstract: A computer-implemented method for correcting artifacts in computed tomography data is provided. The method includes inputting a sinogram into a trained sinogram correction network, wherein the sinogram is missing a pixel value for at least one pixel. The method also includes processing the sinogram via one or more layers of the trained sinogram correction network, wherein processing the sinogram includes deriving complementary information from the sinogram and estimating the pixel value for the at least one pixel based on the complementary information. The method further includes outputting from the trained sinogram correction network a corrected sinogram having the estimated pixel value.

Abstract: A proximity sensor comprises a reference inductor, a first set of sensor inductors, a first set of comparators, each comparator of the first set of comparators corresponding to one of the sensor inductors of the first set of sensor inductors, and an alternating current voltage source to output a sinusoidal voltage to the reference inductor and each of the sensor inductors. Each comparator of the first set of comparators receives a voltage across the reference inductor as a reference voltage and each comparator of the first set of comparators receives a voltage across a corresponding sensor inductor as an input voltage.

Abstract: A leak detection system is provided with a first window configured to mount at a first opening in a first wall portion in an enclosure (e.g., for a gas turbine engine or other equipment in a power plant). The leak detection system includes a leak sensor configured to transmit a beam through the first window and an interior of the enclosure to obtain sensor feedback. The leak detection system includes a controller configured to evaluate the sensor feedback to monitor for a leak of a hazardous fluid in the enclosure.

Abstract: An electronics package includes an electrically insulating substrate having a first surface and a second surface, an adhesive layer positioned on the first surface of the electrically insulating substrate, and an electrical component having a top surface coupled to the adhesive layer on a surface thereof opposite the electrically insulating substrate, the electrical component having contact pads on the top surface. Vias are formed through the electrically insulating substrate and the adhesive layer at locations corresponding to the contact pads by way of a mechanical punching operation, with each of the vias having a via wall extending from the second surface of the electrically insulating substrate to a respective contact pad. At each via, the electrically insulating substrate comprises a protrusion extending outwardly from the first surface thereof so as to cover at least part of the adhesive layer in forming part of the via wall.

Abstract: A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.

Abstract: A turbine engine includes a pressurized fluid source, a duct system comprising a plurality of ducts in fluid communication with the pressurized fluid source, and a duct failure detection system. The duct failure detection system includes a plurality of pressure sensors. Each of the plurality of pressure sensors is in operable communication with two ducts of the plurality of ducts. Each of the plurality of ducts has at least two pressure sensors of the plurality of pressure sensors in operable communication therewith.

Abstract: The current disclosure provides for mapping ultrasound images to resolution mapped ultrasound images using generative neural networks, while maintaining clinical quality of the resolution mapped ultrasound image, thereby enabling a clinician to evaluate ultrasound images in a preferred resolution without loss of clinically relevant content.

Abstract: Exemplary embodiments of the present invention provide a CT imaging method of coronary artery and a computer-readable storage medium, the method comprising: generating and outputting a global optimal phase image of a coronary artery; and generating and outputting a local optimal phase image of a particular trunk of the coronary artery based on a trunk selection command.

Abstract: Various methods and systems are provided for a multi-frequency transducer array. In one example, the transducer array includes an element formed of one or more sub-elements, at least one sub-element having a different resonance frequency. A frequency range of the transducer array may thereby be broadened.

Abstract: A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.

Abstract: The present application provides an inducer seal configured to provide a flow of air to a rotor shaft within a turbine of a gas turbine engine. The inducer seal includes a ring plate having an outer surface with a circumferential channel and an inner surface having an abradable seal. A number of inducer slots are positioned in the ring plate that extend from the outer surface to the inner surface such that the flow of air may pass therethrough in a tangential direction relative to rotation of the rotor shaft to cool the rotor shaft.

Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span. The frangible airfoil portion including a plurality of composite plies and one or more shape memory alloy inserts disposed between the plurality of composite plies. A gas turbine engine including a frangible airfoil and methods for forming a frangible airfoil are also disclosed.

Abstract: Various methods and systems are provided for mammogram imaging. In one example, a method for an x-ray mammography system includes determining, based on a pre-exposure image of a subject acquired with the x-ray mammography system before acquisition of one or more main images, that the subject has an implant; automatically adjusting one or more imaging parameters in response to determining that the subject has the implant; and acquiring the one or more main images with the adjusted one or more imaging parameters.

Abstract: A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.

Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system adjusts parameters of the fuel based on data received from the sensors.

Abstract: A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.