Abstract: Example embodiments relate to containment units usable for safely containing, storing and transporting items such as electric vehicles.

Abstract: A gas turbine engine, comprising a turbomachine and a housing at least partially encasing a portion of the turbomachine, the housing having an inner surface and defining in part a void between the inner surface and the portion of the turbomachine, the housing moveable relative to the portion of the turbomachine; and an engine component selectively coupled to the portion of the turbomachine or to the housing.

Abstract: Methods and compositions are described herein for primer extension target enrichment of immune receptor (BCR or TCR) sequences.

Abstract: Described herein are examples of evaluating electromagnetic energy reflection data of security scans. In embodiments, a method to evaluate electromagnetic energy reflection data determines whether electronic information of a security scan contains an anomaly, and identifies an anomaly location in the electronic information corresponding to the anomaly. The method determines a subset of the electronic information corresponding to the anomaly location, determines anomaly attributes using the subset of the electronic information, and evaluates the anomaly attributes using a database of reference items by comparing anomaly attributes to respective reference characteristics of reference items or identity information. When a comparison meets the respective match criterion for the given reference item, the method assigns to the anomaly the respective identifier as an anomaly identifier.

Abstract: An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.

Abstract: The present disclosure relates to systems for the expression of antibodies or antigen binding fragments in a subject, as well as methods of treatments of diseases therewith.

Abstract: A system and method for automatically trimming and reclassifying workout data is disclosed. The system receives data associated with a workout of a user from at least one sensor associated with the user, the workout being classified as a first type of workout. The system processes the data to identify at least one time interval during the workout that does not correspond to the first workout type. The system prompts the user to select whether to remove or reclassify a subset of the data that is associated with the identified time interval. If the user chooses to do so, the system removes or reclassifies the subset of the data that is associated with the identified time interval. The system generates and provides workout depictions using the data, at least one of which illustrates only the remaining data that was not removed or reclassified.

Abstract: State machine engines are disclosed, including those having an inter-rank bus control system, which may include a register. The state machine engine may include a plurality of configurable elements, such that each of the plurality of configurable elements comprises a plurality of memory cells. These cells may analyze data and output a result of the analysis. The IR bus control system may halt a write operation of data to be analyzed by the cells based, at least in part, on one or more conditions.

Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.

Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, a fan blade, and a counterweight assembly. The fan disk is configured to rotate about an axial centerline of the gas turbine engine when installed in the gas turbine engine. The trunnion is mounted to the fan disk and defines a slot extending through a portion of the trunnion. The fan blade defines a pitch axis and is rotatably attached to the fan disk about its pitch axis through the trunnion. The counterweight assembly includes a link arm extending to the trunnion and an engagement device mounted to the link arm that is disposed to move through the slot of the trunnion.

Abstract: Systems and methods involve a case assembly, stylus, cover assembly, and portable electronic device, the system includes a case assembly including an elongated aperture extending in a first direction through at least one interior wall portion and through at least one second exterior wall portion of a second side, the elongated aperture including an elongated linear dimension being the largest of a plurality of portions of an internal length dimension of an internal base surface of the case assembly; and including a cover assembly including a linear dimension at least as large as the elongated linear dimension of the elongated aperture. In addition, other aspects are described in the claims, drawings, and text forming a part of the present disclosure.

Abstract: State machine engines are disclosed, including those having an inter-rank bus control system, which may include a register. The state machine engine may include a plurality of configurable elements, such that each of the plurality of configurable elements comprises a plurality of memory cells. These cells may analyze data and output a result of the analysis. The IR bus control system may halt a write operation of data to be analyzed by the cells based, at least in part, on one or more conditions.

Abstract: A method is provided for operating a thermal management system of a gas turbine engine. The method includes: operating the gas turbine engine to start-up the gas turbine engine; receiving data indicative of a state of a thermal transport bus of the thermal management system using a sensor, the state of the thermal transport bus including a phase of a thermal fluid within the thermal transport bus; and starting a pump of a pump assembly in response to receiving data indicative of the state of the thermal transport bus of the thermal management system, the pump in fluid communication with the thermal transport bus.

Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, an actuation device, a fan blade, and a counterweight assembly. The trunnion is mounted to the fan disk. The actuation device is operably coupled to the trunnion. The fan blade is rotatably attached to the fan disk. The counterweight assembly includes a link arm, a lever arm, a hinge, and a counterweight. The link arm is connected to the trunnion, to the actuation device, or to both. The link arm is configured to drive rotation of the trunnion relative to the fan disk. The hinge is pivotably connected to the lever arm. The lever arm is connected to the link arm and is disposed to rotate about a connection point of the lever arm and the hinge. The counterweight is mounted to the lever arm at a location spaced from the hinge.

Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.

Abstract: Systems and methods involve implementations such as a first aperture extending through an interior base surface and an exterior base surface, and a second aperture extending through the interior base surface and the exterior base surface, wherein the first aperture includes a first plan-view shape and the second aperture includes a second plan-view shape, the first plan-view shape of the first aperture being different that the second plan-view shape of the second aperture; and a bumper assembly including a first engagement member sized and shaped to couple with the first aperture and the least one second engagement member sized and shaped to couple with the second aperture. In addition, other aspects are described in the claims, drawings, and text forming a part of the present disclosure.