Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.

Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour.

Abstract: An apparatus and method for early page address prediction. For example, one embodiment of a processor comprises: an instruction fetch circuit to fetch a load instruction; a decoder to decode the load instruction; execution circuitry to execute the load instruction to perform a load operation, the execution circuitry including an address generation unit (AGU) to generate an effective address to be used for the load operation; and early page prediction (EPP) circuitry to use one or more attributes associated with the load instruction to predict a physical page address for the load instruction simultaneously with the AGU generating the effective address and/or prior to generation of the effective address.

Abstract: According to an exemplary embodiment of this disclosure, among other possible things a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor section, a plurality of turbine disks in at least one of the compressor section and the turbine sections, at least one cover plate corresponding to at least one of the turbine disks, each of the cover plates includes, at least two snaps connected via a webbing portion, and a bore region radially inward of the at least two snaps and connected to at least one of the at least two snaps via the webbing portion.

Abstract: An apparatus and method for early page address prediction. For example, one embodiment of a processor comprises: an instruction fetch circuit to fetch a load instruction; a decoder to decode the load instruction; execution circuitry to execute the load instruction to perform a load operation, the execution circuitry including an address generation unit (AGU) to generate an effective address to be used for the load operation; and early page prediction (EPP) circuitry to use one or more attributes associated with the load instruction to predict a physical page address for the load instruction simultaneously with the AGU generating the effective address and/or prior to generation of the effective address.

Abstract: Among other things, flow rates of traffic among endpoints in a network are controlled. Notifications are received about flowlets originating or received at the endpoints. Each of the flowlets includes one or more packets that are in a queue associated with a corresponding flowlet. In response to the received notifications, updated flow rates are computed for the flowlets. The updated flow rates are sent to devices for use in controlling flow rates for the flowlets in accordance with the computed updated flow rates.

Abstract: A rotor assembly includes a first rotor, a second rotor mounted on the first rotor and co-rotatable there with, and a thermal shield interlocked with the second rotor for co-rotation there with.

Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.

Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.

Abstract: An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour.

Abstract: A damper seal received in a cavity of a turbine blade located between a platform and a retention shelf damper seal according to an exemplary aspect of the present disclosure includes, among other things, a central body portion having a first end region, an opposing second end region, and a width. The damper seal further includes a first portion extending from the first end region of the central body portion, and a first end region of the first portion includes first outwardly extending tabs that define a first enlarged portion that has a first width greater than the width of the central body portion and a second portion extending from the opposing second end region of the central body portion.

Abstract: In accordance with one aspect of the disclosure, a rotor is disclosed. The rotor may include a disk having a central axis, an airfoil radially extending from the disk, a bayonet tab extending radially from the disk, and a lock. The lock may further include a short tab and a long tab, both extending radially from the disk and in an axial direction with respect to the central axis. The long tab may have a greater axial length than the short tab.

Abstract: A gas turbine engine combustor configured to cool a first vane platform by directing airflow through an aft combustor rail is disclosed. In various embodiments, a gas turbine engine combustor may comprise an aft combustor rail connected between an outer wall of an outer liner and an aft heat shield panel, and a plurality of holes in the aft combustor rail. The aft combustor rail may be positioned near an outer vane platform of a first vane stage of a turbine. Further, the plurality of holes may be designed to focus pass-through airflow onto the outer vane platform. In various embodiments, each hole of the plurality of holes may be angled between 20°-90° relative to the aft combustor rail. Additionally, the plurality of holes may be angled to converge the airflow to a focused area, such as a leading edge vane airfoil of the first vane stage.

Abstract: Among other things, flow rates of traffic among endpoints in a network are controlled. Notifications are received about flowlets originating or received at the endpoints. Each of the flowlets includes one or more packets that are in a queue associated with a corresponding flowlet. In response to the received notifications, updated flow rates are computed for the flowlets. The updated flow rates are sent to devices for use in controlling flow rates for the flowlets in accordance with the computed updated flow rates. Also, rates of flow at endpoints of a network are controlled. A device in the network sends notification of a start or end of a flowlet at an endpoint of the network. The notification is sent to an allocator to which other devices send notifications with respect to other flowlets. At the device, a communication rate is received from the allocator. The rate is one of a set of communication rates for flowlets starting and ending at endpoints of the network.

Abstract: Over the last few decades there has been major innovation in devices that use electricity (cell phones, computers, tablets, televisions), however, there has been little innovation in the mobility and accessibility of electricity itself on the small scale. At the moment, electricity is generally non-transferable on a personal level—if two individuals had cellphones, one at 100% and another at 0%, they could not share the available power between them. The present invention offers a solution to the issue of transferring electricity between cellular devices which enables electricity to be sharable and transferable in small scale daily situations.

Abstract: At the moment, electrical energy production had become a rising problem due to the depletion of fossil fuels, increasing world population, and growing energy consumption per capita. Despite growing research in traditional methods of exploiting electrical energy (steam, wind, water, and nuclear electrical plants) less attention has been given in using human movement as energy source. The present invention will attempt to convert human body movement into electrical energy using electric dynamos.

Abstract: A turbine section has a turbine rotor carrying turbine blades. The turbine blades include seal members at a radially inner location. A vane section is formed of a plurality of circumferentially spaced vane components, each of which has an airfoil extending radially outwardly of a platform. A first seal member is fixed to the platform, and is positioned to be adjacent a seal from a blade which is positioned in one axial direction relative to the first seal member. A second seal member extends circumferentially beyond at least a plurality of the vane components and is positioned to be adjacent a seal member of a blade on an opposed axial side from the first blade. A vane component is also disclosed and claimed.

Abstract: An assembly for a gas turbine engine includes a minidisk that includes an axial extension extending from a disc. The axial extension includes an inner diameter surface and a recess arranged radially opposite the inner diameter surface. The recess provides a radially outwardly extending flange and a bumper extending radially inward from and proud of the inner diameter surface. A method of working on a gas turbine engine section includes inserting a tool into a cavity beneath a seal assembly, and engaging a flange of a minidisk with the tool to manipulate first and second rotors with respect to one another.

Abstract: Described herein are new error-correction (channel) codes: permute codes, iterative ensembles of permute and spinal codes, and graphical hash codes. In one aspect, a wireless system includes an encoder configured to encode data using one of the aforementioned channel codes. The wireless system also includes a decoder configured to decode the encoded data.