Abstract: A system for controlling the flow of fuel to a gas turbine engine is operable in at least two modes. In a first mode, the flow rate of fuel supplied from a fuel source to the combustors of the turbine engine is controlled by modulating the position of a metering valve. A controller determines the controllability of the metering valve and, if it is determined to be non-controllable, then the system is operated in the second mode. In the second mode, the flow rate of fuel supplied to the combustors is controlled by modulating the position of a bypass valve.

Abstract: An electromechanical thrust reverser actuation system that is designed with non-symmetric redundant channels is interfaced with an aircraft engine control system that is also redundantly designed. In one embodiment, the engine control system is also designed with non-symmetric redundant channels, and in another embodiment it is designed with symmetric redundant channels.

Abstract: An improved oil seal is provided for sealing passage of a rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a dynamic oil-air separator and a slinger rotor mounted on the shaft for rotation therewith, the slinger rotor having an outwardly extending slinger ring with an outboard seal face with radially oriented slots and a circumferential groove or grooves.

Abstract: An electric control system and method for operating the cowl doors of an aircraft engine that includes one embodiment with one or more electric motors that are energized to move the cowl doors to the open position. The motor is de-energized and the cowl doors are allowed to close under their own weight, driving the motor and causing it to operate as a generator. An electrical load absorbs the energy generated by the motor while the cowl doors close, thereby limiting the speed at which the doors close.

Abstract: An active magnetic bearing assembly includes at least two rotors and two stator assemblies each having two pole faces. The pole faces of the stator assemblies are axially offset from the pole faces of their associated rotors. Thus, axial control of a shaft that is rotationally mounted using the active magnetic bearing assembly is provided by a reluctance centering force.

Abstract: A multi-stage pilot valve is disclosed for selectively supplying a working fluid to and venting from a reaction jet main stage actuation chamber. In a preferred embodiment of the invention, the pilot valve comprises a solenoid actuated ball and socket flapper valve having a pressure inlet, an exhaust outlet and a service port. The first stage service port is in fluid communication with a second stage actuation chamber. A piston disposed in the second stage actuation chamber operatively engages a ball member of a ball-and-seat type valve comprising the second stage valve. The second stage valve also comprises a pressure inlet, an exhaust outlet and a service port. The piston and ball are sized relative to each other such that when the second stage actuation chamber is pressurized by the first stage, the force is sufficient to seat the ball against the second stage pressure inlet.

Abstract: A thrust reverser system that has one or more moveable thrust reverser components for redirecting the thrust of a jet engine. The thrust reverser system has a torque limiter coupled between synchronization mechanisms that mechanically couple actuators used to drive the thrust reverser. The torque limiter reduces the potential for the transmission of excessive torque between thevdifferent moveable thrust reverser components, and reduces the likelihood of secondary system damage due to a jam in the system. Thus, the cost and/or weight associated with each of the components comprising the system may be reduced.

Abstract: A novel and inventive hand held powder-fed laser fusion welding torch providing manual flexibility for laser welding with powder-fed material. The hand held laser includes a body, handle, and nozzle assembly. The nozzle may be shrouded by a cover that is slightly spaced apart from the nozzle. The gap between the two may provide space through which inert gas may flow. Laser light from a remote source shines through the nozzle's central aperture. The nozzle aperture may be circumscribed by powder channel outlets aligned upon a working focal point coincident with the laser beam to treat a workpiece. A proximity sensor may enable selective welding torch operation according to the presence of a workpiece.

Abstract: An improved stationary roller shaft of a gear assembly for an air turbine starter is provided. The air turbine starter may be used to start a gas turbine engine, such as may be found in aircraft, ships and military vehicles. The stationary roller shaft is formed of a material having a hardness of at least 66 Rockwell C and having a low inclusion content rating, thereby providing improved wear and/or fatigue properties.

Abstract: A system and method of supplying temperature-controlled air to an aircraft environmental control system during ground support operations that uses an air amplifier to control the flow rate of cooling air through a heat exchanger. A heat exchanger removes heat from a flow of compressed air supplied to the air conditioning unit and supplies cooled compressed air at a predetermined temperature. The flow of the cooled compressed air is controlled by using the air amplifier.

Abstract: A system for controlling one or more jet engine thrust reversers includes a motor, a speed sensor, and a controller circuit. The motor is coupled to one or more jet engine moveable thrust reverser components for moving the one or more moveable thrust reverser components to at least a deployed position. The speed sensor is operable to sense the a rotational speed of the motor. The controller circuit has an output coupled to the motor for selectively energizing and deenergizing the motor in response to the speed sensor sensing that the rotational speed of the motor is, respectively, at or above a first predetermined rotational speed and at or below a second predetermined rotational speed. The system controls the deployment operation of the jet engine thrust reversers such that unwanted mechanical and electrical loads are avoided.

Abstract: A capacitance pressure sensor includes a pressure diaphragm, an acceleration diaphragm, and a support member. The pressure diaphragm and acceleration diaphragm each include electrodes on surfaces that face each other, thereby forming a pressure sensitive capacitor. The pressure sensitive capacitor is coupled to the support member, which is in turn directly coupled to a base plate. The structure of the pressure sensor is simplified structure in that it includes no additional stress isolation components.

Abstract: One or more particle arrestor rings are mounted in a curved radial flow portion of a gas turbine annular flow passage. The arrestor rings block line of sight paths between the turbine wheel and the annular flow passage outlet. Thus, the arrestor rings substantially inhibit relatively high energy particles from exiting the gas turbine housing, thus substantially inhibiting collateral damage to surrounding equipment and structure.

Abstract: A system for controlling one or more jet engine thrust reversers includes a motor, a position sensing device, and a controller circuit. The motor is coupled to one or more jet engine thrust reverser moveable components for moving the one or more thrust reverser moveable components to at least a stowed position. The position sensing device is operable to sense at least when the one or more thrust reverser moveable components attain a predetermined position relative to the stowed position. The controller circuit has an output coupled to the motor so the motor rotates at a variable speed in response to a position sensing device that senses when the predetermined position is attained. The system controls the stowage operation of the jet engine thrust reversers such that structural damage is avoided, and/or a limit cycle condition is prevented, and/or engagement of stow locks is assured.

Abstract: A method of restoring a damaged surface of a substrate to a functional condition through a filler material consisting essentially of tungsten disulfide and epoxy resin having a 10:1 ratio by weight. The filler material is cured after being applied to the damaged surface by uniformly raising the temperature to a cure temperature of the epoxy to allow any volatiles to evaporate without the creation of voids in the surface such that the resulting porosity prevents corrosion of the substrate when exposed to aromatic fuels at temperatures of 350 degrees F. The filler material consists of tungsten disulfide and a two part epoxy such as Hysol EA 9394/C-2.

Abstract: A coupling with a tribological system that can withstand temperatures up to 600° C. The coupling includes a shaft having an outer surface with a layer of chromium and a sleeve for receiving the shaft. The sleeve has an inner surface with a layer of silver or gold. The silver or gold layer contacts the chromium layer to form the tribological system.

Abstract: A system for controlling one or more jet engine thrust reversers includes a motor, a speed sensor, and a controller circuit. The motor is coupled to one or more jet engine moveable thrust reverser components for moving the one or more moveable thrust reverser components to at least a deployed position. The speed sensor is operable to sense the a rotational speed of the motor. The controller circuit has an output coupled to the motor for selectively energizing and deenergizing the motor in response to the speed sensor sensing that the rotational speed of the motor is, respectively, at or above a first predetermined rotational speed and at or below a second predetermined rotational speed. The system controls the deployment operation of the jet engine thrust reversers such that unwanted mechanical and electrical loads are avoided.

Abstract: A ceramic ball bearing assembly (20) has raceway components generally held in residual compression by accompanying metal attachments. In a ceramic ball bearing assembly (20), an outer raceway (22) is formed that is held in compression by a circumscribing steel ring. The components may be fitted together with the ceramic raceway subject to thermal contraction while the steel ring is subject to thermal expansion. Upon mating, the ceramic raceway (22) slightly expands while the steel ring slightly contracts to impose residual compression upon the ceramic raceway. The residual compression preserves the ceramic raceway despite thermal or other stresses of operating environment. An inner ceramic raceway (24) is constructed by employing one of several of the herein described methods, and the ceramic ball bearing assembly of the present invention may use balls (26), needles, cylinders, or other rolling elements in order to achieve smooth angular translation between the inner and outer ceramic raceways.

Abstract: A thrust reverser system includes one or more actuators each having an integrated locking mechanism that prevents unintended actuator movement, and thus unintended thrust reverser movement. Each of the actuators with the integrated locking mechanism includes a housing, a drive shaft, and a lock. The drive shaft includes an outer surface, is rotationally mounted within the housing, and is operable, in response to the operation of the one or more motors, to rotate in a first rotational direction, to thereby move the thrust reverser to the deploy position, and a second rotational direction, to thereby move the thrust reverser to the stow position. The lock is movably mounted within the housing and is operable to move between at least a first position and a second position, and includes at least a side surface and a bottom surface. One or more gears are provided on the outer surface of the drive shaft, each of which is adapted to mesh with gears that are operably coupled to the thrust reverser.

Abstract: An electric thrust reverser actuation system includes an electric motors that is controlled to operate in both a motoring mode and a generating mode. During normal actuation system operations, the electric motor is controlled to operate in the motoring mode to move one or more moveable thrust reverser components. During a power interrupt event, in which the motor's primary power source is lost, the motor is controlled to operate in the generating mode. The electrical power generated by the motor during its operation in the generating mode maintains the thrust reverser system locking mechanisms in an energized, unlocked condition, thereby preventing damage to system components.