Abstract: A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.

Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.

Abstract: Antibody molecule-drug conjugates (ADCs) that specifically bind to lipopolysaccharides (LPS) are disclosed. The antibody molecule-drug conjugates can be used to treat, prevent, and/or diagnose bacterial infections and related disorders.

Abstract: A rotary machine, such as a turbomachine of a gas turbine engine, for example, including a rotor and a rotor seal assembly. The rotor is rotatable about a rotational axis and has a rotor seal face. The rotor seal assembly includes a seal body, one or more primary fluid conduits formed in the seal body, and a retraction assembly. The seal body has a seal face and is positionable to form a fluid-bearing gap between the seal face of the seal body and the rotor seal face. The one or more primary fluid conduits are fluidly connected to the fluid-bearing gap to supply a fluid to the fluid-bearing gap. The retraction assembly is connected to the seal body to move the seal body in a retraction direction away from the rotor seal face.

Abstract: A turbine engine having a rotor rotatable about a rotational axis, a stator, a plurality of circumferentially spaced bleed air passages, and an inducer. The plurality of circumferentially spaced bleed air passages being located between an axially adjacent set of vanes of the stator and blades of the rotor. The inducer including a nozzle passage fluidly coupling a nozzle inlet of the inducer to a nozzle outlet of the inducer.

Abstract: A heat exchanger is provided. The heat exchanger includes a first wall manifold. The heat exchanger further includes a second wall manifold spaced apart from the first wall manifold. The heat exchanger further includes a plurality of vanes that extend generally circumferentially between the first wall manifold and the second wall manifold. The heat exchanger further includes a plurality of fluid circuits defined within the heat exchanger. Each fluid circuit in the plurality of fluid circuits includes an inlet channel portion and an outlet channel portion defined within the first wall manifold. A return channel portion defined within the second wall manifold. At least one passage portion of a plurality of passage portions defined within each vane of the plurality of vanes. The at least one passage portion extends between the return channel portion and one of the inlet channel portion and the outlet channel portion.

Abstract: A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.

Abstract: A method and system for estimating the ground state energy of a quantum Hamiltonian. The disclosed algorithm may run on any hardware and is suited for early fault tolerant quantum computers. The algorithm employs low-depth quantum circuits with one ancilla qubit with classical post-processing. The algorithm first draws samples from Hadamard tests in which the unitary is a controlled time evolution of the Hamiltonian. The samples are used for evaluating the convolution of the spectral measure and a filter function, and then inferring the ground state energy from this convolution. Quantum circuit depth is linear in the inverse spectral gap and poly-logarithmic in the inverse target accuracy and inverse initial overlap. Runtime is polynomial in the inverse spectral gap, inverse target accuracy, and inverse initial overlap. The algorithm produces a highly-accurate estimate of the ground state energy with reasonable runtime using low-depth quantum circuits.

Abstract: A bite-proof spout is disclosed which contains multiple durometer material, such that the higher durometer material is in closer contact to the mouth of a user to be able to withstand biting without undue deterioration than the lower durometer material which is positioned further away from the mouth.

Abstract: A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.

Abstract: The inbred rice line designated DG263L is disclosed. Embodiments include the seeds of inbred rice line designated DG263L, the plants of inbred rice line designated DG263L, plant parts of inbred rice line designated DG263L, and methods for producing a rice plant produced by crossing rice DG263L with itself or with another rice variety. Embodiments include methods for producing a rice plant containing in its genetic material one or more genes or transgenes and the transgenic rice plants and plant parts produced by those methods. Embodiments also relate to rice cultivars, breeding cultivars, plant parts, and cells derived from inbred rice line designated DG263L, methods for producing other rice cultivars, lines or plant parts derived from inbred rice line designated DG263L, and the rice plants, varieties, and their parts derived from use of those methods. Embodiments further include hybrid rice seeds, plants, and plant parts produced by crossing DG263L with another rice cultivar.

Abstract: A turbine engine having a stator, a rotor, and a seal assembly. The rotor being rotatable about a rotational axis. The seal assembly having a carriage assembly, a seal body and a biasing element. The carriage assembly being carried by the stator. The carriage assembly defining a seal cavity. The seal body being provided within the seal cavity.

Abstract: A cassette to dispense a pleated tubing. The cassette includes a circular body having an annular channel housing and a pull tab and pull strip. At least one wall has an upper end with a lip disposed thereon. An annular cover is attached to the lip at the upper end defining a gap over the annular body. A tubing is disposed within the annular channel housing and withdrawn from the gap. At least one of a plurality of apertures is provided at a lower end of the annular channel housing. The apertures are adapted to be aligned with a projection extending upward from within a container.

Abstract: A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.

Abstract: A thermal management system for a gas turbine engine includes a heat exchanger including first and second sides, with the first side in contact with flow path air flowing through a flow path of the engine. Furthermore, the system includes a housing positioned relative to the heat exchanger such that the housing and the second side of the heat exchanger define a plenum configured to receive bleed air from the engine. Moreover, the system includes and at least one of a plurality of fins extending outward from the second side of the heat exchanger in a radial direction into the plenum and along the second surface of the heat exchanger in the circumferential direction or an impingement plate defining a plurality of impingement apertures, with each impingement aperture configured to direct an impingement jet of the bleed air within the plenum onto the second side of the heat exchanger.

Abstract: A turbine engine comprising an engine core having a rotor and a stator, and a floating seal assembly sealing at least portions of the rotor and the stator relative to a higher-pressure area and a lower-pressure area. The floating seal assembly can comprise a carriage assembly at least partially defining a seal cavity and a seal body floating within the seal cavity. The floating seal assembly can further include at least one of a seal located between the seal body and the carriage assembly, and a seal face located between the seal body and the carriage assembly.

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: Conformance testing of a rebuilt motor includes disposing a motor under test in a motor test stand, coupling a plurality of sensors to the motor under test including a first vibrational sensor to the motor under test; a first temperature sensor to the motor under test; a first rotational speed sensor to the motor under test. A set of test parameters are received comprising parameters for a conformance test, the test parameters including a vibrational sensor parameter, a temperature sensor parameter, and a rotational speed parameter. A motor under test is placed in an on-state and a processing device receives sensor data simultaneously from the sensors, determines that the rotational speed satisfies the rotational speed parameter, and stores time sampled sensor data received from the plurality of sensors relative to a time zero corresponding to a time when the rotational speed satisfies the rotational speed.

Abstract: A thermal management system for a gas turbine engine includes a heat exchanger including first and second sides, with the first side in contact with flow path air flowing through a flow path of the engine. Furthermore, the system includes a housing positioned relative to the heat exchanger such that the housing and the second side of the heat exchanger define a plenum configured to receive bleed air from the engine. Moreover, the system includes and at least one of a plurality of fins extending outward from the second side of the heat exchanger in a radial direction into the plenum and along the second surface of the heat exchanger in the circumferential direction or an impingement plate defining a plurality of impingement apertures, with each impingement aperture configured to direct an impingement jet of the bleed air within the plenum onto the second side of the heat exchanger.