Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

Abstract: A data processing apparatus is provided that includes a plurality of storage elements. Receiving circuitry receives a plurality of incoming data beats from cache circuitry and stores the incoming data beats in the storage elements. At least one existing data beat in the storage elements is replaced by an equal number of the incoming data beats belonging to a different cache line of the cache circuitry. The existing data beats stored in said plurality of storage elements form an incomplete cache line.

Abstract: A data processing apparatus is provided. Cache circuitry caches data, the data being indexed according to execution contexts of processing circuitry. Receive circuitry receives invalidation requests each referencing a specific execution context in the execution contexts. Invalidation circuitry invalidates at least some of the data in the cache circuitry and filter circuitry filters the invalidation requests based on at least one condition and, when the condition is met, causes the invalidation circuitry to invalidate the data in the cache circuitry.

Abstract: A rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends radially from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform, a first cooling hole that extends circumferentially between a mate face of the platform and the second cooling core, a second cooling hole that extends between a gas path surface of the platform and the second cooling core, the second cooling core radially disposed between the gas path surface and a non-gas path surface, and the second cooling core circumferentially disposed between the first cooling core and the mate face. A method of cooling a blade is also disclosed.

Abstract: A data processing apparatus is provided, which includes a cache to store operations produced by decoding instructions fetched from memory. The cache is indexed by virtual addresses of the instructions in the memory. Receiving circuitry receives an incoming invalidation request that references a physical address in the memory. Invalidation circuitry invalidates entries in the cache where the virtual address corresponds with the physical address. Coherency is thereby achieved when using a cache that is indexed using virtual addresses.

Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.

Abstract: A multi-user collaboration system. User-specific change markings are applied to a collaboration object. The user-specific changes to be presented are time-oriented, based on a time of a last view of the collaboration object. A plurality of users that have access to the collaboration object are identified. Time-ordered versions of the collaboration object are captured. Each captured version corresponds to changes made to the collaboration object by any of the users. When a request to view the collaboration object is received from a subject user, a method determines the latest version of the collaboration object and also determines the specific last accessed version of the collaboration object that was seen by the subject user. The two versions are compared, and the comparison changes are used to generate user-specific change markings. The collaboration object with the generated user-specific change markings is presented by rendering the user-specific change markings on respective user-specific devices.

Abstract: A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

Abstract: An assembly according to an exemplary aspect of the present disclosure includes, among other things, a disk, a cover plate providing a cavity at a first axial side of the disk, a passageway including an inlet provided by a notch in at least one of the disk and the cover plate in fluid communication with the cavity, and the passageway extending from the inlet to an exit provided at a second axial side of the disk opposite the first axial side, the exit in fluid communication with the inlet, and the passageway configured to provide fluid flow from the cavity to the exit.

Abstract: A pre-diffuser for a gas turbine engine includes an exit guide vane ring having a multiple of exit guide vanes defined around an engine longitudinal axis; a hot fairing structure adjacent to the exit guide vane ring to define a multiple of diffusion passages around the engine longitudinal axis; an outer radial interface between a radial outer surface of the hot fairing structure and the exit guide vane ring, the outer radial interface being a full hoop structure; and an anti-rotation feature between the hot fairing structure and the exit guide vane ring, the anti-rotation features inboard of the multiple of diffusion passages.

Abstract: A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts; and a multiple of diffusion passage ducts attached to the ring-strut-ring structure. A pre-diffuser for a gas turbine engine includes an exit guide vane ring having a multiple of exit guide vanes defined around an engine longitudinal axis; a ring-strut-ring structure adjacent to the exit guide vane ring to form a multiple of diffusion passages defined around the engine longitudinal axis, an inlet to each of the multiple of diffusion passages smaller than an exit from each of the multiple diffusion passage through the ring-strut-ring structure; a diffusion passage duct attached to the ring-strut-ring structure at the exit from each of the multiple diffusion passage.

Abstract: A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts and a multiple of inlets to a respective diffusion passage, one of the multiple of inlets formed between each one of the multiple of hollow struts located between two diffusion passages.

Abstract: A gas turbine engine component array includes first and second components each having a platform. The platforms are arranged adjacent to one another and provide a gap. A seal is arranged circumferentially between the first and second components and in engagement with the platforms to obstruct the gap. A cooling hole is provided in the seal and is in fluid communication with the gap. The cooling hole has an increasing taper toward the gap.

Abstract: A diffuser case assembly for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case.

Abstract: A computer-implemented system and method include a rate-limiting server. The server receives a request from a client and uses an early stage process to search for a rate-limiting token bucket (TB) using metadata associated with the request. Responsive to finding the TB using the first metadata, a response operation is performed. Responsive to not finding the TB using the first metadata, a late stage process is used to search for the rate-limiting TB using server-side session data associated with the request. Responsive to not finding the TB using the session data, the TB is created and associated with at least two search indexes comprising the first metadata associated with the request and the session data. Finally, the response operation is performed that comprises transmitting a determined response to the client.

Abstract: An apparatus and method are provided for imaging and analyzing images of tissue samples. The apparatus includes an imager, a lighting system, and a processor. The imager is configured to capture images within a selectable field of view. A tissue sample container is positionable within the field of view. The imager is configured to capture images of a plurality of tissue sample containers. The lighting system is configured to illuminate the field of view. The processor is configured to receive a first plurality of captured images of tissue sample containers. The processor is configured to analyze the first plurality of captured images and to determine whether there is tissue missing from any ones of the first plurality of captured images.

Abstract: A gas turbine engine rotor assembly includes a plurality of blades spaced apart from each other for rotation about an axis. Each of the blades includes a platform having an inner surface and an outer surface. Adjacent platforms are separated from each other by a gap. A damper is positioned at an offset position within the gap to contact the inner surfaces of the adjacent platforms.

Abstract: A 5G network communicates per-slice constraints for QoS parameter values from a centralized unit (CU) to a MAC scheduler of a distributed unit (DU). The CU communicates these per-slice constraints, rather than or in addition to per-DRB constraints, to the MAC scheduler over the CU/DU interface. In some implementations, the CU/DU interface is an F1 air interface as defined in specification 38.473 in the 3GPP standard. In some implementations, the DU provides per-slice performance feedback over the CU/DU interface. Based on such feedback, the CU may adjust the per-slice QoS constraints.

Abstract: An apparatus is provided for scanning and decoding barcodes in a tray or other container containing multiple items, such as tissue samples, that are identified with discrete barcodes. The apparatus includes an imager, a lighting system, and a processor. The imager is configured to capture images within a selectable field of view. At least a portion of a bulk sample container, which is configured to carry a plurality of sample/tissue containers, is positioned within the field of view. The lighting system is configured to evenly light the field of view. The processor is configured to receive the captured images from the imager. The processor is further configured to analyze a first image of the captured images and to detect and decode the barcodes present in the first image.

Abstract: A gas turbine engine component comprises a blade having a leading edge and a trailing edge. The blade is mounted to a disc and configured for rotation about an axis. A platform supports the blade, and has a fore edge portion at the leading edge and an aft edge portion at the trailing edge. At least one of the fore edge portion and aft edge portion includes a mouth portion defined by an inner wing and an outer wing spaced radially outward of the inner wing. At least one coverplate is retained against the disc by the inner wing. A gas turbine engine is also disclosed.