Abstract: Plasma viewports for high-temperature environments in semiconductor processing equipment are disclosed; such viewports may use a triple-window design, with each window providing particular functionality.

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: 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: Systems involve a case assembly including a base, a first side extending from the base, and a stand assembly including an elongated member having an elongated cavity, and a base extending from the elongated member. The stand assembly is rotatably coupled with the case assembly so that the stand assembly is rotatable between a first rotational position and a second rotational position so that the elongated cavity is covered by the case assembly when the stand assembly is in the first rotational position, and so that the elongated cavity is at least partially uncovered from the case assembly when the stand assembly is in the second rotational position. Other aspects are described in the claims, drawings, and text forming a part of the present disclosure.

Abstract: Plasma viewports for high-temperature environments in semiconductor processing equipment are disclosed; such viewports may use a triple-window design, with each window providing particular functionality.

Abstract: An example method to characterize an anomaly includes obtaining information about an item using a first mode scan and detecting whether the item contains an anomaly based on the information. The method further includes determining, responsive to detecting the anomaly, an area of interest of the item corresponding to a location of the anomaly, and determining a strategy including a procedure to obtain other information of the area of interest. The method refines a characterization of the anomaly based on the other information, and compares the characterization of the anomaly to a predetermined criterion. The method iteratively revises the strategy to perform additional available procedures, to further refine the characterization of the anomaly. When the characterization of the anomaly meets the predetermined criterion corresponding to a prohibited item, the method identifies the anomaly as prohibited.

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, 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: An example method to characterize an anomaly includes obtaining information about an item using a first mode scan and detecting whether the item contains an anomaly based on the information. The method further includes determining, responsive to detecting the anomaly, an area of interest of the item corresponding to a location of the anomaly, and determining a strategy including a procedure to obtain other information of the area of interest. The method refines a characterization of the anomaly based on the other information, and compares the characterization of the anomaly to a predetermined criterion. The method iteratively revises the strategy to perform additional available procedures, to further refine the characterization of the anomaly. When the characterization of the anomaly meets the predetermined criterion corresponding to a prohibited item, the method identifies the anomaly as prohibited.

Abstract: A gas turbine engine is provided.

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 method for saving a file stored on a third-party system to a cloud storage system includes receiving, at a cloud storage server of the cloud storage system, a save request from the third party system. The method further includes authenticating the save request, based at least in part on information identifying a user, creating a copy of the file at the cloud storage server, and associating the copy of the file with the user.

Abstract: A means and method to enhance the security of personalized and variable print-on-demand data on vital records or documents, such as checks, by inkjet printing. A specially formulated penetrating ink prints information on the front side to create an indelibly seamless “dual image” on the reverse side. The reverse image symbiotically complements the primary image on the print side to provide ease of authentication and tamper resistance. Specially formulated MICR ink is used to print information on the front side. Specially formulated penetrating may be different color. Either invisible ultraviolet fluorescent penetrating ink or visible penetrating ink may be used to create the image on the reverse side. The print side and reverse side are printed using single-pen printing by orienting inkjet two different pens in a series.

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: A case system includes (I) a first material component including (A) at least one aperture including at least one edge, (B at least one border portion extending from the at least one edge of the aperture, and (C) at least one elongated portion. The case system also includes (II) a second material component including (A) at least one aperture plug portion extending through the at least one aperture of the first material component, and (B) at least one edge portion extending from the plug portion, wherein the at least one border portion of the first material and the at least one edge portion of the second material are coupled via co-molding, and wherein the first material component is co-molded before the co-molding with the second material component. Other aspects are described in the claims, drawings, and text forming a part of the present disclosure.

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.