Abstract: A nacelle assembly includes an inlet lip section and an airfoil adjacent to the inlet lip section. The airfoil is selectively moveable between a first position and a second position to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly.

Abstract: A vehicle includes a vehicular frame, a utility bed, and a passenger restraint assembly. The utility bed is coupled with the vehicular frame and includes a bed floor, a side wall, and a rear scat. The passenger restraint assembly includes a securing member, a belt and a retractor. The securing member is coupled with the utility bed adjacent to the rear seat. The belt includes a first end; a second end, and a securing portion. The securing portion is configured for selective engagement with the securing member. The retractor is coupled with the side wall. The retractor includes a carrier that is coupled with the first end of the belt and is configured to facilitate selective dispensation of the belt.

Abstract: An application server provides a portal application for provisioning one or more controlled communication systems, such as a virtual PBX's hosted on a server in a network environment through a portal application. The virtual PBXs are provisioned in response to data input in a particular PBX language. The portal application includes a viewer-and-controller module for presenting a graphical user interface (GUI) to a client containing fields for accepting user input pertaining to PBX provisioning requirements. An API interface module for communicating with the virtual PBXs includes a wrapper module which translates between normalized data for use by the viewer-and-controller module and data in the particular PBX language for any virtual PBX, and a provisioning module for communicating with the wrapper module.

Abstract: A gas turbine engine system for an aircraft includes a nacelle having a fan cowl with an inlet lip section and a core cowl, at least one compressor and at least one turbine, at least one combustor between the compressor and the turbine, a bleed passage, and a controller. The bleed passage includes an inlet for receiving a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The controller identifies an operability condition and selectively introduces the bleed airflow near a boundary layer of the inlet lip section in response to the operability condition.

Abstract: A turbofan engine deicing system includes a core nacelle (12) housing a turbine. A turbofan (20) is arranged upstream from the core nacelle. A controller (50) manipulates the turbofan in response to detecting an icing condition for avoiding undesired ice buildup on the turbofan engine (10) and nacelle parts. In one example, a variable area nozzle (40) is actuated to generate pressure pulses or a surge condition to break up any ice buildup. The icing condition can be determined by at least one sensor (52) and/or predicted based upon icing conditions schedules.

Abstract: A gas turbine engine includes an accessory gearbox within an engine pylon. The accessory components may be mounted within the engine pylon to save weight and space within the core nacelle as well as provide a relatively lower temperature operating environment.

Abstract: The invention relates to a turbine engine that includes a spool supporting at least one of a compressor and a turbine. A turbofan is coupled to the spool The spool is arranged in a core nacelle, and the turbofan is arranged upstream from the core nacelle. A fan nacelle surrounds the turbofan and the core nacelle and provides a bypass flow path. A structure extends radially between the core and fan nacelles to support the core nacelle relative to the fan nacelle. Surfaces are supported relative to the fixed structure and are moveable between closed and open positions to selectively obstruct bypass flow through the bypass flow path, thereby changing the effective area of the exit nozzle. A change in the effective area of the nozzle exit can be used to improve the efficiency and operation of the turbine engine.

Abstract: A flexible hinge including a first set of plies and a second set of plies, and a hinge area where the first set of plies and the second set of plies bend. A damping material is disposed between plies of the first set and the second set at least at the hinge area thereof to control the deployment of the hinge.

Abstract: A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.

Abstract: A vehicle includes a vehicular frame, a utility bed, and a passenger restraint assembly. The utility bed is coupled with the vehicular frame and includes a bed floor, a side wall, and a rear scat. The passenger restraint assembly includes a securing member, a belt and a retractor. The securing member is coupled with the utility bed adjacent to the rear seat. The belt includes a first end; a second end, and a securing portion. The securing portion is configured for selective engagement with the securing member. The retractor is coupled with the side wall. The retractor includes a carrier that is coupled with the first end of the belt and is configured to facilitate selective dispensation of the belt.

Abstract: A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.

Abstract: A gas turbine engine system for an aircraft includes a nacelle having a fan cowl with an inlet lip section and a core cowl, at least one compressor and at least one turbine, at least one combustor between the compressor and the turbine, a bleed passage, and a controller. The bleed passage includes an inlet for receiving a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The controller identifies an operability condition and selectively introduces the bleed airflow near a boundary layer of the inlet lip section in response to the operability condition.

Abstract: A nacelle assembly for a gas turbine engine includes a fan cowl disposed about an axis, a core cowl within the fan cowl and a bleed passage having an inlet that receives a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The bleed airflow is selectively introduced near a boundary layer of an inlet lip section of the fan cowl.

Abstract: A control system for a turbofan comprises a variable area nozzle for regulating core flow through the turbofan, an actuator, a temperature sensor, a flight controller and a nozzle control. The actuator is coupled to the variable area nozzle to regulate the core flow by positioning the variable area nozzle. The temperature sensor is positioned in the turbofan to sense a gas path temperature of the core flow. The flight controller is connected to the turbofan to make a thrust demand based on a flight condition of the turbofan. The nozzle control is connected to the flight controller and the actuator for directing the actuator based on the gas path temperature and the flight condition, such that the gas path temperature is controlled by adjusting the variable area nozzle to regulate the core flow while the turbofan meets the thrust demand.

Abstract: A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.

Abstract: An apparatus for creating a musical composition comprising an audio interface, and audio converter module, and a multi-track compositor module is disclosed. The audio interface operably receives audio from an audio input device and outputting audio to an audio output device. The audio converter module is operably connected to the audio interface to convert audio received via the audio interface into an audio track having one or more partitions. The multi-track compositor module is configured to receive a first audio track and a second audio track and automatically score each partition of the first and second audio tracks based on one or more criteria. The multi-track compositor module is then configured to construct a third audio track from the partitions of the first and second audio tracks based on the scores for each partition. A method is also provided.

Abstract: A turbofan engine (10) employs a flow control device (41) that changes an effective exit nozzle area (40) associated with a bypass flow path (B) of the turbofan engine. A spool (14) couples a fan (20) to a generator (52). The turbofan emergency power system includes a controller (50) that communicates with the flow control device (41). Upon sensing an emergency condition, the controller manipulates the flow control device to reduce the effective nozzle exit area (40) of the bypass flow path, which chokes the flow through the bypass flow path thereby increasing the rotational speed of the fan. In this manner, the generator is driven at a higher rotational speed than if the flow through the bypass flow path was not choked, which enables a smaller generator to be utilized.

Abstract: A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates synchronizing ring segments relative the static ring to adjust segments of the flap assembly to vary the annular fan exit area and vector the thrust through asymmetrical movement of the thrust vectorable FVAN segments. In operation, adjustment of the entire periphery of the thrust vectorable FVAN in which all segments are moved simultaneously to maximize engine thrust and fuel economy during each flight regime. By separately adjusting the segments of the thrust vectorable FVAN, engine trust is selectively vectored to provide, for example only, trim balance or thrust controlled maneuvering.

Abstract: Disclosed are compounds of formula (I): wherein R3, R5, R7 and R8 are defined herein, which are useful as inhibitors SYK kinase and are thus useful for treating diseases resulting from inappropriate mast cell activation, which include allergic and inflammatory diseases. Also disclosed are pharmaceutical compositions comprising these compounds and processes for preparing these compounds.

Abstract: (A1)) A turbofan engine includes core and fan nacelles that provide a bypass flow path having a nozzle exit area. The bypass flow path carries a bypass flow to be expelled from the nozzle exit area. A turbofan is arranged within the fan nacelle and upstream from the core nacelle for generating the bypass flow. A flow control device includes a surface in the bypass flow path including an aperture. The flow device is adapted to introduce a fluid into the bypass flow path for altering a boundary layer of the bypass flow that effectively changes the nozzle exit area. In one example, bleed air is introduced through the aperture. In another example, pulses of fluid from a Helmholz resonator flow through the aperture. By decreasing the boundary layer, the nozzle exit area is effectively increased. By increasing the boundary layer, the nozzle exit area is effectively decreased.