Abstract: Some example embodiments are directed to an apparatus for performing integrated scheduling in a cloud-based virtualized radio access network (vRAN) architecture including one or more central units (CUs) configured to communicate with one or more remote units (RUs) over an x-haul transport network. The apparatus is configured to determine time-varying channel constraints based on a condition of an access link between the one or more RUs and one or more user equipment (UEs), the access link being in one of a wireless or wireline network, determine x-haul capacity constraints based on an amount of capacity available on an x-haul link between the one or more CUs and the one or more RUs, the x-haul link being in the x-haul transport network, and jointly schedule transmissions to the one or more UEs based on the time-varying channel constraints and the x-haul capacity constraints.

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 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 damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.

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 rotor blade according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, a first cooling core that extends at least partially inside the airfoil, a second cooling core inside of the platform and a first cooling hole that extends between a mate face of the platform and the second cooling core.

Abstract: A gas turbine engine rotor assembly has 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. The inner surfaces of adjacent platforms define a pocket having a radially outer wall, a pressure side wall, and a suction side wall. The pocket includes a leading edge wall portion and a trailing edge wall portion, and a shelf extending in a tangential direction relative to the axis from the pressure side of the pocket. The shelf is spaced apart from the radially outer wall.

Abstract: Approaches to delivering video in a chroma sampling format with a higher chroma sampling rate (such as a YUV 4:4:4 format) using a video encoder and decoder that operate on video in another chroma sampling format with a lower chroma sampling rate (such as YUV 4:2:0) are described. A video decoder can recover stationary content in video at the higher chroma sampling rate, even when the video is encoded and decoded at the lower chroma sampling rate, without significantly increasing bit rate. In some example implementations, the approaches preserve chroma information from pictures in a higher-resolution chroma sampling format, while leveraging commercially available codecs adapted for a lower-resolution chroma sampling format such as YUV 4:2:0, which is widely supported in products.

Abstract: A data processing apparatus is provided including queue circuitry to respond to control signals each associated with a memory access instruction, and to queue a plurality of requests for data, each associated with a reference to a storage location. Resolution circuitry acquires a request for data, and issues the request for data, the resolution circuitry having a resolution circuitry limit. When a current capacity of the resolution circuitry is below the resolution circuitry limit, the resolution circuitry acquires the request for data by receiving the request for data from the queue circuitry, stores the request for data in association with the storage location, issues the request for data, and causes a result of issuing the request for data to be provided to said storage location.

Abstract: A system and method are described for determining if power lines have been damaged. A virtual circuit is established between a control unit and a remote response unit. A signal is transmitted from the remote response unit responsive to a prior signal transmitted by the control unit. Based on a comparison of measurements of the response signal to expected values, a determination is made as to whether or not the line has been damaged.

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.

Abstract: Techniques are described for remuxing multimedia content received in a digital video broadcasting format without performing transcoding of the video and/or audio content. For example, a computing device with a digital television tuner can receive multimedia content in a digital video broadcast format. The computing device can remux the received multimedia content from the digital video broadcasting format in which the multimedia content is received into a target streaming protocol for streaming to other devices. Remuxing operations can comprise demultiplexing the received multimedia content to separate the audio and video content, performing meta-data reconstruction, and multiplexing the audio and video content into a target stream using a target streaming protocol format.

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 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: 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 gas turbine engine includes a turbine section that has a disk rotatable about an axis. The disk has circumferentially-spaced blade mounting features and radially outer rim surfaces extending circumferentially between the blade mounting features. Turbine blades are mounted circumcumferentially around the disk in the blade mounting features. Seals are arranged radially outwards of the disk adjacent the radially outer rim surfaces such that there are respective passages between the seals and the radially outer rim surfaces. The radially outer rim surfaces include radially-extending protrusions that extend into the respective passages.

Abstract: A turbine section comprises a rotor, blade and rim seal. The rotor comprises a rim defining an outer diameter surface, and a slot in the outer diameter surface. The blade comprises an airfoil, a platform surrounding the airfoil, a shank extending from the platform, a root extending from the shank for connecting to the slot, and a nub extending from the shank beneath the platform. The rim seal is disposed between the outer diameter surface and the nub. A method for cooling an outer diameter of a rotor disk comprises bleeding cooling air in a gas turbine engine, passing the flow of cooling air through a cover plate that retains a seal plate against the rotor disk, leaking the cooing air between a rotor disk rim and the seal plate, and guiding the cooling air across an outer diameter surface of the rotor disk rim utilizing a rim seal.

Abstract: A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a component. The component includes a platform having a mateface on a circumferential side thereof. The platform including a core passageway configured to communicate fluid to the mateface.

Abstract: A gas turbine engine component has first and second components each having a platform with an upper surface and a lower surface and with a plurality of side faces extending between the upper and lower surfaces. The platforms are arranged adjacent to one another such that one side face of the platform faces a mating side face of an adjacent platform. At least one cooling hole is formed within the platform and has an inlet to receive a cooling flow and an outlet at least at one of the side faces. The at least one cooling hole increases in size in a direction toward the outlet. A method of cooling a gas turbine engine is also disclosed.