Abstract: A tip turbine engine assembly includes an engine support structure with a rear case, exit guide vanes, an exhaust mixer, and engine mounts. The rear case is disposed about an engine centerline. The exit guide vanes extend radially inwardly from the rear case. The exhaust mixer extends in a flow path of a combustor to mix a high energy gas stream from the combustor with bypass air from a bypass fan. The engine mounts are located on the periphery of the rear case for mounting the engine to an aircraft. The rear case, exit guide vanes, exhaust mixer, and engine mounts form a unitary engine support structure which is installable as a single piece into an engine.

Abstract: A system is provided comprising a computer system, a configuration database, and a dynamic network interfaces application that receives a message from a network access component containing a request to authenticate a client device accessing a network service, determines that a policy requires the client device to be associated with a virtual local area network to access the network service, and authenticates the client device for association with the virtual local area network. The dynamic network interfaces application also searches the configuration database for configuration information to provision the virtual local area network, assigns the configuration information to the client device, the network access component, and a firewall component, and sends a reply containing the configuration information to the network access component and the firewall component in response to the request, wherein the configuration information comprises settings to provision the virtual local area network.

Abstract: A turbine engine includes a compressor section, a combustor arranged in fluid-receiving communication with the compressor section, a turbine section arranged in fluid-receiving communication with the combustor and a gearbox assembly coupled to be driven by the turbine section. The gearbox assembly is located at an axial position that is aft of the compressor section.

Abstract: An inlet guide vane assembly includes an active control feedback system and a plurality of inlet guide vanes. The inlet guide vanes are variable between a plurality of positions. Each of the plurality of inlet guide vanes is positioned in response to an output of the activate control feedback system.

Abstract: A dynamic network policies system based on device classification is provided. The system comprises a computer system, a configuration database, and a dynamic network policies application based on device classification that receives a message from a virtual local area network access component containing a device identity certificate. The application parses the device identity certificate to discover a device classification, references the configuration database to determine a network policy associated with the device classification, and associates the network policy with a virtual local area network definition. The application also sends a reply containing the virtual local area network definition to the virtual local area network access component in response to the request, wherein access to network services is made available by association with a virtual local area network, and wherein association with a virtual local network is specific to the device classification and the network policy.

Abstract: An integrally bladed rotor has an outer rim with a plurality of blades extending radially outwardly of the outer rim. A plurality of channels are formed radially inwardly of the outer rim. A discontinuity formed at a radially outer surface of the outer rim includes a first thin slot at a radially outer face of the outer rim with an enlarged seal holding area. A second thin slot is positioned radially inwardly of the seal holding. The first and second thin slots are thinner circumferentially than the enlarged seal holding area. A seal is inserted into the seal holding area. The seal does not extend into the first and second thin slots, nor into the channels.

Abstract: A gas turbine engine system includes a fan assembly, a low pressure compressor, a low pressure turbine, a plurality of engine cores including a first engine core and a second engine core, and a control assembly. A primary flowpath is defined through the fan assembly, the low pressure compressor, the low pressure turbine, and the active engine cores. Each engine core includes a high pressure compressor, a combustor downstream from the high pressure compressor, and a high pressure turbine downstream from the combustor. The control assembly is configured to control operation of the plurality of engine cores such that in a first operational mode the first and the second engine cores are active to generate combustion products and in a second operational mode the first engine core is active to generate combustion products while the second engine core is idle.

Abstract: A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.

Abstract: Methods and systems for a mesh-network takeover are provided. In one embodiment, a first controller having a first attribute and a first group of nodes in its network receives a message from a node in the first group. The message indicates that the node in the first group received a signal from a node that is in a second group and associated with a second controller having a second attribute. Further, the message includes the second attribute. Responsive to receiving the message, the first controller compares the first attribute with the second attribute. As a result of comparing the first attribute with the second attribute, the first controller makes a determination that it has a lower priority than the second controller. Responsive to making the determination, the first controller no longer communicates with the first group, resulting in at least one node in the first group joining the second network.

Abstract: A gearbox support assembly for a turbine engine includes an epicyclic gear arrangement and a first tapered bearing and a second tapered bearing spaced apart from the first tapered bearing. The first tapered bearing and the second tapered bearing support the epicyclic gear arrangement.

Abstract: A processor-implemented method for providing application single sign on leveraging a virtual local area network identifier is provided. The method comprises an authentication server providing a client device access to a network via association with a virtual local area network and a credential. The method also comprises the device invoking an application hosted on an application server and the application server identifying a virtual local area network tag associated with the device. The method also comprises the application server sending a message to the authentication server requesting linkage of the tag with a user identification associated with the device. The method also comprises the authentication server linking the tag with the user identification associated with the device and sending a message to the application server containing the identification.

Abstract: A fan-turbine rotor assembly includes one or more turbine ring rotors. Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring includes axial installation and radial locking of each turbine ring rotor.

Abstract: A turbine engine includes a plurality of variable fan inlet guide vanes. Where the turbine engine is a tip turbine engine, the variable fan inlet guide vanes permit the ability to control engine stability even though the fan-turbine rotor assembly is directly coupled to the axial compressor at a fixed rate. The fan inlet guide vanes may be actuated from an inner diameter of the fan inlet guide vanes.

Abstract: A tip turbine engine provides increased efficiency while eliminating or reducing the number of axial compressor stages by moving the core airflow inlet aft of the fan. As a result, the core airflow entering the core airflow inlet is the fan exhaust, which is already at an increased pressure. A portion of the fan exhaust is guided radially inward, then axially forward and then radially outward through compressor chambers in the hollow fan blades for further, centrifugal compression.

Abstract: A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring (114) includes axial installation and radial locking of each turbine ring rotor.

Abstract: A gas turbine engine is provided with a first heat exchanger associated with a cooling air flow to deliver cooling air to a turbine section. A second heat exchanger is associated with a fuel supply line for delivering fuel into a combustion section. An intermediate fluid cools air at the first heat exchanger and heats fuel at the second heat exchanger.

Abstract: To manage playout of digital media by a media player, a wireless communication device (WCD) will include partitioned data storage including discrete partitions having distributor-modules corresponding with various media distributors, and including a digital rights management (DRM) controller. When the media player seeks to play media, it will request a DRM key from the WCD. The DRM controller may then identify the appropriate distributor-module and request the key from the distributor-module. If the distributor-module possesses the key, it will return it for transmission to the media player. Otherwise, the distributor-module may engage in secure communication with a provisioning system to obtain the DRM key and may then return the key. Upon receipt of the key, the media player may then play the media.

Abstract: A tip turbine engine (10) provides first and second turbines (32) rotatably driven by a combustor (30) generating a high-energy gas stream. The first turbine (32) is mounted at an outer periphery of a first fan (24a), such that the first fan is rotatably driven by the first turbine (32a). The second turbine (32b) is mounted at an outer periphery of a second fan (24b), and is rotatably driven by the high-energy gas stream. In one embodiment, the first turbine (32a) rotatably drives a plurality of stages of first compressor blades (54) in an axial compressor (22) in a first rotational direction, while the second turbine (32b) rotatably drives a plurality of stages of second compressor blades (52) in the axial compressor (22) in a second rotational direction opposite the first. By rotatably driving alternating stages of compressor blades in opposite directions, the efficiency of the axial compressor (22) is increased and/or the number of stages of compressor blades can be reduced.

Abstract: A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or educing the number of axial compressor (122) stages by moving the core airflow inlet (27) aft of the fan (24). As a result, the core airflow entering the core airflow inlet is the fan exhaust, which is already at an increased pressure. A portion of the fan exhaust is guided radially inward, then axially forward and then radially outward through compressor chambers (72) in the hollow fan blades (28) for further, centrifugal compression.

Abstract: A method for cooling components of a gas turbine engine, having first and second sets of components that require cooling, includes removing thermal energy from cooling air, directing the cooling air from which thermal energy has been removed to the first set of components of the gas turbine engine, and transferring thermal energy away from the second set of components of the gas turbine engine using a vaporization cycle of a vapor cooling assembly. Use of the vaporization cycle offsets thermal energy removed from the cooling air.