A defect depth estimation system includes a training system and an imaging system that performs defect depth estimation from a monocular 2D image without using a depth sensor. The training system repeatedly receives a first type of image having a defect, and a second type of image that captures the target object having the defect and provides ground truth data indicating an actual depth of the defect. The training system transforms the first domain and the second domain into a target third domain that reduces a domain gap and trains a machine learning model to learn the actual depth of the defect using the target third domain. The imaging system receives a 2D test image in the first forma and uses the trained machine learning model to determine an estimation of the actual depth of the actual defect and to output estimated the estimation of the actual depth.
A high-entropy alloy includes a single-phase, face centered cubic structure composition containing between 43.0 and 49.9 at% nickel, between 16.0 and 26.0 at% chromium, between 6.5 and 16.5 at% iron, between 1.5 and 4.5 at% molybdenum, between 2.0 and 7.5 at% aluminum and between 6.5 and 11.0 at% cobalt. Such compositions are good replacements for more expensive nickel-based alloys and have good strength and corrosion resistance properties.
Embodiments of the present disclosure generally relate to aircraft engines and, more particularly, to detecting defects in aircraft engines using visual neuromorphic sensors. In some embodiments, an event associated with a portion of an aircraft engine may be identified based on a change on a visual data characteristic from a visual neuromorphic sensor. In response to identifying the event associated with the portion of the aircraft engine, synchronous data from a synchronous data collection sensor coupled to the aircraft engine may be retrieved for a predetermined period of time, and a defect associated with the aircraft engine detected based on the identified event and the synchronous data. Other embodiments may be disclosed or claimed.
A plating method includes: providing a nickel-containing plating solution; immersing a metallic substrate in the plating solution; and applying a voltage between the substrate and an anode to apply a plating. The providing comprises blending chromium powder with a precursor of the plating solution so that the plating solution is a Cr-containing plating solution. The as-applied plating forms a layer containing chromium particles from the powder.
A test system (20) has: a base (30); first and second support posts (40A, 40B) extending upward from the base; and a crosshead (44) receiving the first and second support posts. The crosshead is movable along a vertical range of motion relative to the first and second support posts and lockable to the first and second support posts within that range of motion. An actuator (70) provides a vertical force between the base and the locked crosshead. The vertical force is converted to a horizontal force on a specimen (26).
An apparatus with a communication system includes a method of operating the communication system. The communication system includes first device at a first location, a radio frequency transceiver at the first device, a waveguide extending between the first device to a second device at a second location, and a processor. The processor is configured to transmit a first radio frequency signal through the waveguide toward the second location, receive a second radio frequency signal in response to the first radio frequency signal, determine a presence of a fault in the waveguide from the second radio frequency signal, and transmit a third radio frequency signal via the radio frequency transceiver outside of the waveguide when the presence of the fault is determined.
A wall assembly (60) for use in a combustor (56) of a gas turbine engine, the wall assembly (60) including: a support shell (68, 70); a liner panel (72, 74); and an annular grommet (115) extending from the liner panel (72, 74) the annular grommet (115) defining a dilution passage (116) and the annular grommet (115) extends through an opening (117) in the support shell (68, 70) when the support shell (68, 70) and the liner panel (72, 74) are secured to each other, the annular grommet (115) having a top portion (119) that defines a portion of a periphery of the opening (117); and a backstop (121) extending from the top portion (119) of the annular grommet (115), the backstop (121) defining another portion of the periphery of the dilution passage (116) and the backstop (121) extending through and above the opening (117) in the support shell (68, 70) when the liner panel (72, 74) is secured to the support shell (68, 70).
An apparatus (50) for repairing a defective area in a polyimide composite (54) component includes a flexible film (56) enclosure for covering the defective area (52) of the polyimide composite component; a seal (62) around a perimeter of the film; a resin injection assembly (60) for injecting resin between the flexible film enclosure and the defective area of the component; and a vacuum source (58) for drawing vacuum between the flexible film enclosure and the component. A method is also disclosed.
B29C 73/02 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using liquid or paste-like material
A coated article (20) has: a substrate (22); a bond coat (26) deposited on the substrate; and a mixed stabilizer layer (30) positioned over the bond coat. The mixed stabilizer has matrix oxide(s) of one or more matrix tetravalent elements and stabilizer oxides of at least two stabilizer trivalent elements. The matrix elements are selected from a first group consisting of Zr, Hf, Ti, and Ce. The stabilizer elements are selected from a second group consisting of La, Ce, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Y, and Sc.
A turbine vane assembly for a gas turbine engine is disclosed herein. The turbine vane assembly includes a turbine vane including a leading edge, a pressure edge, a suction edge, and a trailing edge, a core defined by the turbine vane, an outer platform end wall connected to the turbine vane, the outer platform end wall defining an interior space, the interior space being in fluid communication with the core, and a plurality of cooling holes formed in the turbine vane, the plurality of cooling holes being in fluid communication with the core.
A method of additive manufacturing of a component is provided and includes building up the component to have a first uppermost layer and a foundation to have a second uppermost layer below the first uppermost layer, evacuating powder from around the component and the foundation to expose the second uppermost layer, disposing, on the second uppermost layer, a forged flange having an upper surface coplanar with the first uppermost layer, backfilling powder about the component and the forged flange and completing a building up of the component by building up on the forged flange.
B33Y 80/00 - Products made by additive manufacturing
B22F 7/08 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools with one or more parts not made from powder
An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that is expanded through a turbine section for powering a primary propulsor. The aircraft propulsion system further includes a tap that is at a location upstream of the combustor section where a bleed airflow is drawn, a heat exchanger where the bleed airflow is heated by the gas flow, a power turbine through which heated bleed airflow is expanded to generate a work output, and a secondary propulsor that is driven by the work output that is generated by the power turbine.
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
B64D 27/02 - Aircraft characterised by the type or position of power plants
B64D 27/12 - Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, wings
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
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