Abstract: A technique for controlling access to one or more attractions is achieved using a number of access keys, each being issued to one or more users. An electronic queue management part manages a virtual queue in respect of each attraction and receives electronic requests for attraction access, each request relating to an access key and being for the users associated with it to access a particular attraction. Receipt of each request causes the respective users to be added to a corresponding virtual queue. A time at which each group of users reaches the front of the virtual queue and can access the attraction is determined. The users access the attractions by presenting an access key to an access control part, in communication with the electronic queue management part. Only a user presenting an access key at the correct time for accessing the attraction is allowed access to the attraction.

Abstract: A technique for controlling access to one or more attractions is achieved using a number of access keys, each being issued to one or more users. An electronic queue management part manages a virtual queue in respect of each attraction and receives electronic requests for attraction access, each request relating to an access key and being for the users associated with it to access a particular attraction. Receipt of each request causes the respective users to be added to a corresponding virtual queue. A time at which each group of users reaches the front of the virtual queue and can access the attraction is determined. The users access the attractions by presenting an access key to an access control part, in communication with the electronic queue management part. Only a user presenting an access key at the correct time for accessing the attraction is allowed access to the attraction.

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Abstract: Apparatus is disclosed for determining the weight of tobacco in a tobacco product (10), the tobacco product comprising a tobacco component (16) and a plurality of non-tobacco components (12, 14, 18, 20, 22). The apparatus comprises means (26) for determining the total weight of the tobacco product (10), means (30) for producing an x-ray image of the tobacco product, means (34) for determining weights of the non-tobacco components from the x-ray image, and means (34) for determining the weight of the tobacco component based on the total weight of the tobacco product and the weights of the non-tobacco components. This may allow an accurate determination of tobacco weight to be achieved. Furthermore, measurements can be taken where components are present which might interfere with microwave measurements.

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Abstract: The invention relates to a combination of a TLR-9 agonist and a conjugate of Formula (I) or pharmaceutically acceptable salt thereof.

Abstract: The present invention generally relates to a glycopeptide conjugate compound of Formula (I):, as described herein, compositions comprising the conjugate compound and to the use of such a compound to as a vaccine.

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Abstract: A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter.

Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.

Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.

Abstract: A gas turbine engine system and method of operating gas turbine engines are provided. The gas turbine engine assembly includes a gas turbine engine includes a power shaft configured to rotate about an axis of rotation. The gas turbine engine assembly also includes a first fan and a second fan coupled to the power shaft coaxially with the gas turbine engine. The gas turbine engine assembly also includes a first fan duct configured to direct a first stream of air to the first fan. The gas turbine engine assembly also includes a second fan duct configured to direct a second stream of air to the second fan. The gas turbine engine assembly also includes an exhaust duct configured to direct a stream of exhaust gases of the gas turbine engine in a direction of the axis of rotation.

Abstract: A gas turbine engine composite article having a composite article airfoil extending outwardly to an article root to an article airfoil tip. Within the article airfoil is a core including a core airfoil attached to a core root including a core dovetail. A continuous outer three-dimensional braided layer including braided composite material tows are braided on the core and the braided layer covers the entire core airfoil and the core root. The core may be an inflatable mandrel or a composite core made of a composite material. The core may include stiffeners such as an I beam or hollow rectangular cross-section box beams. A method for making such an article includes braiding a continuous outer three-dimensional braided layer including braided composite material tows on the core including covering the entire core airfoil and the core root with the continuous outer three-dimensional braided layer.

Abstract: A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter.

Abstract: A technique for controlling access to one or more attractions is achieved using a number of access keys, each being issued to one or more users. An electronic queue management part manages a virtual queue in respect of each attraction and receives electronic requests for attraction access, each request relating to an access key and being for the users associated with it to access a particular attraction. Receipt of each request causes the respective users to be added to a corresponding virtual queue. A time at which each group of users reaches the front of the virtual queue and can access the attraction is determined. The users access the attractions by presenting an access key to an access control part, in communication with the electronic queue management part. Only a user presenting an access key at the correct time for accessing the attraction is allowed access to the attraction.

Abstract: Composite airfoil singlet, includes airfoil extending from base to tip of airfoil, integrally formed with no more than one outer platform at tip and/or no more than one inner platform at base. Parallel composite plies or woven fibers extend through airfoil and through outer and/or inner platforms. Outer and/or inner curved sections extend between outer and/or inner platforms and airfoil respectively. Assembly includes circular row of the composite airfoil singlets depending radially inwardly from and mounted to an outer shroud or casing. Outer and/or inner fasteners may secure outer and inner platforms to outer shroud or casing and an inner shroud respectively and include shanks extending substantially perpendicularly from outer and inner fastening plates though platform holes in outer and inner platforms and through outer and inner holes in outer shroud or casing and inner shroud respectively. Nuts are screwed on threaded ends of shanks.

Abstract: A propulsion system for an aircraft includes at least two propulsion engines. Each propulsion engine rotates about a longitudinal rotational axis, and a propulsive fan associated with each propulsion engine rotates in a plane perpendicular to the longitudinal rotational axis. Each plane is at least one of spaced axially along a fuselage of the aircraft and canted such that each plane does not intersect any other plane associated with another propulsion engine and propulsive fan.

Abstract: A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter.

Abstract: A method of making a hollow metal component comprising the steps of providing at least one core comprising a first side and a reverse side; utilizing a first metal spray process to apply at least one metal or metal alloy to the first side of the core, resulting in a partially-formed structure comprising a first side and a reverse side; and utilizing a second metal spray process to apply at least one metal or metal alloy to the reverse sides of the partially-formed structure and the core, resulting in a rough structure. A hollow metal component comprising a first side having interior and exterior surfaces, a reverse side having interior and exterior surfaces, the interior surfaces of the first side and the reverse side defining at least one cavity. The component is integrally formed and has regions comprising relatively different material compositions, the regions having gradual transitions of materials therebetween.