Abstract: An intra-oral device for manipulating the musculus uvulae and uvula is provided comprised of a support member attached to a dental splint having a means to regulate the musculus uvulae and uvula by use of an adjustment bend and about parallel and rear configuration, a method manipulating the tissue of the musculus uvulae and the uvula to bring about relief for snoring, sleep apnea and other similar or related disorders to improve a patient's health by maintaining unblocked air passage from the oropharynx to the nasopharynx.

Abstract: A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The portion of the nacelle assembly including the adjustable contour is selectively moveable between a first portion and a second position to influence the adjustable contour of the nacelle assembly. A controller identifies an abnormal aircraft operating condition and selectively moves the portion of the nacelle assembly including the adjustable contour between the first position and the second position in response to detecting the abnormal aircraft operating condition.

Abstract: A gas turbine engine comprises a plurality of fan rotors. A gas generator comprises at least one compressor rotor, at least one gas generator turbine rotor, a combustion section, and a fan drive turbine downstream of at least one gas generator turbine rotor. A shaft is configured to be driven by the fan drive turbine. The shaft engages gears to drive the plurality of fan rotors. A system controls the amount of power supplied to the plurality of fan rotors. A method of operating a gas turbine engine is also disclosed.

Abstract: Systems and methods for altering airflow to gas turbine engines are provided. In this regard, a representative system includes a gas turbine engine inlet having a slat, the slat being movable between a retracted position and an extended position. In the extended position, the slat increases an effective diameter of the inlet compared to the diameter of the inlet when in the retracted position.

Abstract: An example method of thermal energy exchange within a turbomachine includes heating a liquid using thermal energy from compressed air, injecting the liquid into a first portion of a turbomachine, and using the compressed air to cool a second portion of the turbomachine.

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: The invention relates to a holding means (1) for fastening a portable communication device to a vehicle component, in particular to a windscreen of a motor vehicle, the holding means (1) comprising a basic carrier (3) for carrying the portable communication device such that the portable communication device extends parallel to a front face (24) of the basic carrier (3). The basic carrier (3) comprises a pair of holding arms (11, 12) arranged on opposite sides of the front face (24) of the basic carrier (3) and extending perpendicular to the front face (24) and parallel to each other. The holding arms (11, 12) are arranged for accommodating the portable communication device between them, wherein the basic carrier (3) furthermore comprises an elastic coupling element (18) by means of which the holding arms (11, 12) are joined to each other.

Abstract: Disclosed are compounds, compositions and methods for treating various diseases, syndromes, conditions and disorders, including pain. Such compounds are represented by Formula (I) as follows: wherein R1, R2, R3, Q, and G are defined herein.

Abstract: Disclosed are compounds, compositions and methods for treating various diseases, syndromes, conditions and disorders, including pain. Such compounds are represented by Formula I as follows: wherein R1, R2, R3, Q, and G are defined herein.

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: 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: A nacelle assembly includes an inlet lip section having a highlight diameter and a throat diameter. One of the highlight diameter and the throat diameter is fixed and the other of the highlight diameter and the throat diameter is selectively adjustable in each of a first direction and a second direction relative to the inlet lip section to influence a contraction ratio associated with the inlet lip section.

Abstract: Disclosed are compounds, compositions and methods for treating various diseases, syndromes, conditions and disorders, including pain. Such compounds are represented by Formula I as follows: wherein R1, R2, R3, Q, and G are defined herein.

Abstract: Disclosed are compounds, compositions and methods for treating various diseases, syndromes, conditions and disorders, including pain. Such compounds are represented by Formula (I) as follows: wherein R1, R2, R3, Q, and G are defined herein.

Abstract: A turbofan engine includes a core nacelle housing a spool having a turbine. A turbofan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the turbofan and core nacelle. A bifurcation supports the core nacelle relative to the fan nacelle and extends radially between the nacelles. The core and fan nacelles provide a bypass flow path receiving bypass flow from the turbofan. In the example, the nacelles provide a fixed nozzle exit area. The bifurcation includes an inlet that is in communication with a passage. The passage is selectively opened and closed by a valve to provide air from the inlet to a vent opening near the nozzle exit area. By opening the valve, the nozzle exit area is effectively increased to provide increased bypass flow through the turbine engine.

Abstract: An example method of thermal energy exchange within a turbomachine includes heating a liquid using thermal energy from compressed air, injecting the liquid into a first portion of a turbomachine, and using the compressed air to cool a second portion of the turbomachine.

Abstract: This disclosure relates to a gas turbine engine including a core engine that drives a fan. A fan nacelle surrounds the fan and provides an inner surface facing the fan. The fan nacelle includes an inlet lip adjoining the inner surface. A ring is arranged at the inner surface and is axially upstream from the fan. The ring includes a deployed position in which the ring is spaced radially inwardly from the inner surface to provide a gap therebetween through which air flows. The ring also includes a stowed position in which the ring is arranged radially inwardly from the deployed position and proximate to the inner surface. The ring is commanded to the deployed position in response to detecting a first condition, which corresponds to a flow separation condition at the fan nacelle inlet. The ring may be stowed during cruise conditions, for example.

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 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.

Abstract: A disclosed gas turbine engine includes a core engine defined about an engine centerline axis, the core engine including a compressor section driven through a shaft by a turbine section. A core nacelle surrounds the core engine and a fan nacelle is mounted at least partially around the core nacelle to define a fan bypass flow path for a bypass airflow. A fan section disposed within the fan nacelle is driven by the turbine section of the core engine through a geared architecture. An engine pylon supports the core nacelle and the fan nacelle. A towershaft is driven by the shaft of the core engine and drives a generator mounted within the core nacelle. The generator powers an electric motor mounted within the engine pylon. The electric motor drives a plurality of accessory components that are also mounted within the engine pylon.