Abstract: A method for balancing blades of a wind turbine comprises several steps. First, vibration sensor readings are taken while wind turbine blades are in a pre-balancing configuration. These vibration sensor readings are used to determine initial blade imbalance. Next, vibration sensor readings are taken while wind turbine blades are in a first and a second pitch offset configuration. These vibration sensor readings are used to determine system response to the first and second pitch offset configurations. A correction pitch configuration is determined from the initial blade imbalance and the system response. Finally, blades of the wind turbine are pitched according to the correction pitch configuration.

Abstract: A bleed air conditioning system within an aircraft including a low-pressure bleed air line and a high-pressure bleed air line. The system includes an air-to-air heat exchanger and an un-cooled bleed air line to connect the air-to-air heat exchanger to the low-pressure bleed air line and the high-pressure bleed air line. The un-cooled bleed air line carries a flow of un-cooled bleed air from at least one of the low-pressure bleed air line and the high-pressure bleed air line to the air-to-air heat exchanger. The system also includes a cooled bleed air line connected to the air-to-air heat exchanger for carrying cooled bleed air from the air-to-air heat exchanger and a low-pressure bypass line connecting the low-pressure bleed air line to the cooled bleed air line, bypassing un-cooled bleed air from the low-pressure line around the air-to-air heat exchanger to the cooled bleed air line.

Abstract: A permanent magnet comprises a primary winding, a secondary winding, a permanent magnet, an output terminal for connection to an external load, and a switching mechanism with two modes. In a first mode of the switching mechanism, the primary winding is connected between neutral and the output terminal, and the varying magnetic flux from the permanent magnet induces a nonzero voltage at the output terminal. In the second mode, the secondary winding provides a return path to neutral for the primary winding, thereby providing negligible voltage and current at the output terminal and substantially canceling change in magnetic flux from the permanent magnet.

Abstract: An integrated electronic engine control and environmental control system bleed control apparatus for use with an aircraft engine. The apparatus comprises an electronic engine controller, an environmental control system bleed controller for controlling a flow of bleed air from the aircraft engine to an environmental control system located in an aircraft fuselage, and a housing for mounting on or near the aircraft engine. The housing contains both the electronic engine controller and the environmental control system bleed controller.

Abstract: A bleed valve module for mounting to a support structure within an aircraft includes a pipe, a plurality of bleed valves connected to the pipe, a plurality of pneumatic actuators connected to the plurality of bleed valves, and a vibration isolating element. The pipe contains a flow of bleed air and includes a plurality of inlets and an outlet. The plurality of bleed valves controls the flow of bleed air in the pipe. The plurality of pneumatic actuators actuate the plurality of bleed valves. The vibration isolating element connects the bleed valve module to the support structure within the aircraft and isolates the bleed valve module from vibration.

Abstract: A starter for an auxiliary power unit includes a direct current motor operably connectable to an auxiliary power unit. A clutch is arranged in an electrically parallel relationship and configured to operably connect the motor to the auxiliary power unit when engaged, the motor and the clutch powered by a common input line. A time delay switching element is located and configured to delay power delivery to the direct current motor thus providing for full engagement of the clutch prior to initiation of rotation of the motor.

Abstract: A valve release mechanism has an actuator, a ring, a plurality of ball bearings, and a retainer. The retainer is positioned adjacent an inner diameter of the ring and has a plurality of circumferentially spaced holes therein. Each circumferentially spaced hole receives one of the plurality of ball bearings, which are movable therein. The ring has channels and lands along its inner diameter that allow the ball bearings to move varying distances relative to the retainer. The lands contact the ball bearings when the ring is in a first position and the channels receive the ball bearings when the ring is in a second position. The poppet has a groove that is vertically aligned with circumferentially spaced holes in the retainer when the poppet is in a first closed position. The ball bearings are pressed into the groove in the poppet by the lands of the ring. The resulting interference of the ball bearings with poppet locks the poppet in the first closed position.

Abstract: A system comprises a package with top and bottom surfaces, a plurality of high-power transient voltage suppressors arranged within the package, and a robust lead frame. Each of the transient voltage suppressors has first and second major surfaces substantially perpendicular to the top and bottom surfaces of the package. The lead frame comprises leads connected to the major surfaces of the transient voltage suppressors. Each of the leads has a thickness greater than about 0.015 inches (or 0.381 mm) in a mounting portion, in order to dissipate heat from the transient voltage suppressors and to resist vibration-induced stress on the package.

Abstract: A power distribution system and method has a controller and at least one semiconductor switch. The power distribution system additionally has an on status detector which detects the status of the semiconductor switches, and an overcurrent status circuit which checks for overcurrent conditions.

Abstract: A gas turbine engine sealing arrangement which includes a combustor liner establishing a combustion area and a turbine nozzle configured to receive a portion of a combustor liner. A sealing ring arrangement is configured to seal with the turbine nozzle to control fluid flow from the combustion area and reduce leakage.

Abstract: An electric load damper assembly includes a synchronous generator operable to provide a plurality of phases of electrical output in response to a mechanical input from a rotating shaft. An electric load damper includes a phase leg for each of the plurality of phases. Each phase leg includes a resistive load, a snubber and at least one solid state switch. The at least one solid state switch is in parallel with the snubber, and the at least one solid state switch and snubber are collectively in series with the resistive load. A controller is operable to receive a signal indicative of a rotational speed oscillation of the synchronous generator, and is operable to selectively reduce a torsional oscillation of the shaft by diverting electrical current from the synchronous generator through the resistive load of each of the plurality of phases in response to the signal exceeding a predefined threshold.

Abstract: An example filter assembly prevents particles from entering a control valve and defines an airflow path between an inlet and outlet. An inlet tube extends from an inlet and defines an inlet passage into a filter housing. Openings within the inlet tube open into an interior space of a filter housing. An outer housing defines a cavity within which the filter housing is secured. The filter housing includes an open top portion that engages a cap that covers and seals the outer housing. The cap holds the filter housing to prevent movement of the filter housing.

Abstract: A rotor assembly for a miniature gas turbine propulsion system comprises a centrifugal compressor wheel, a turbine wheel, a shaft and a tie bolt. The centrifugal compressor wheel includes a first curved tooth coupling, and the turbine wheel includes a second curved tooth coupling interconnected with the first curved tooth coupling. The shaft extends from the centrifugal compressor wheel, and the tie bolt extends between the shaft and the turbine wheel to bring the first curved tooth coupling into compression with the second curved tooth coupling. As such, the compressor wheel and the turbine wheel are assembled and remain, over the operational envelope of the propulsion system, in a reliably robust aligned configuration.

Abstract: A laminated heat exchanger includes at least one heat exchange layer that includes a plurality of side members that define a frame having an interior portion. A plurality of heat exchange members extend between at least two of the plurality of side members across the interior portion. The plurality of heat exchange members are linked by a ligament member to form a heat exchange member chain.

Abstract: A method for monitoring a fuel supply system for a turbine engine, the fuel supply system comprising a fuel pump and a pressure regulation valve configured to receive fuel from an outlet of the fuel pump includes determining by a bypass monitor an amount of bypass flow in a bypass path located between the pressure regulation valve and an inlet of the fuel pump; determining an amount of leakage flow in the fuel supply system by the bypass monitor based on the bypass flow; and determining whether the leakage flow exceeds a predetermined threshold by the bypass monitor, and in the event the leakage flow exceeds the predetermined threshold, indicating a need for maintenance of the fuel supply system.

Abstract: A deployable ram air turbine assembly includes a rotatable turbine, a drivetrain mechanically connected to the rotatable turbine, and a flux regulated permanent magnet generator operably connected to the drivetrain.

Abstract: An aircraft electrical system comprises a generator to be driven as part of a gas turbine engine. The generator supplies electrical power to a plurality of accessories associated with the gas turbine engine, and to an aircraft power bus in parallel to the supply to the accessories. A control detects a short circuit on the aircraft power bus. When a short circuit is detected on the aircraft power bus, a switch is driven open to disconnect the aircraft power bus from the generator. In this manner, the power will continue to be delivered to the plurality of accessories. In a separate feature, a control voltage is provided by an auxiliary permanent magnet generator to a voltage regulator for the main generator.

Abstract: A surface cooler includes a base plate, and at least one fin element extending from the base plate. The at least one fin element includes an outer surface portion that is configured and disposed to be in direct contact with a first fluid and an inner surface portion that is configured and disposed to be in direct contact with a second fluid. The at least one fin element defines a primary heat exchange member that is configured and disposed to facilitate an exchange of heat between the first and second fluids.

Abstract: A carbon dioxide (CO2) removal system includes first and second sorbent beds, a heat exchange system and means for reducing pressure. The sorbent beds each have a solid amine sorbent for adsorbing and desorbing CO2. At a given time, one of the sorbent beds adsorbs CO2 and the other sorbent bed desorbs CO2. The heat exchange system cools the CO2 adsorbing bed and heats the CO2 desorbing bed so that the temperature of the CO2 desorbing bed is greater than the temperature of the CO2 adsorbing bed. The means for reducing pressure reduces CO2 pressure at the CO2 desorbing bed. A method for removing CO2 includes supplying a gas stream to a sorbent bed containing a solid amine sorbent to adsorb CO2, reducing pressure at another sorbent bed to desorb CO2, heating the CO2 desorbing bed, cooling the CO2 adsorbing bed, and removing CO2 from the CO2 desorbing bed.

Abstract: An electric motor for a fuel pump is provided with a shutdown switch positioned intermediate an inverter, and its control coil. In this location, the shutdown function can be achieved without heavy components. In another feature, when the fuel pump is shut down, a signal is sent upstream to a voltage regulator associated with a generator, such that the voltage supplied downstream by the generator can be reduced to eliminate any potential voltage spike due to the shutdown of the electric motor. The electric motor with shutdown switch enables low weight fault tolerant flux regulated machines.