Abstract: A method for removing particulates from a fluid, the method including the steps of: producing a laminar flow of the fluid through a single-flow passageway defined by an interior surface of an outer rotor of a centrifuge; and imparting centrifugal force on the fluid in a direction orthogonal to a direction of the flow of the fluid to capture the particulates from the fluid. The method may further comprise rotation of the centrifuge at a speed of 5,000 to 15,000 revolutions per minute. The method may also or alternatively comprise locating the interior surface between 3 and 5 inches from an axis of rotation of the centrifuge.

Abstract: An apparatus for determining the fluid level of a container, such as an accumulator, may include both a remote quantity indicator and a direct quantity indicator. The remote quantity indicator may include a remote dial at the end of a flexible cable or an electrical signal receiver receiving an electrical signal from a rotary variable differential transformer (RVDT), such as a potentiometer. The RVDT type of indicator may include an electrical connector on the accumulator to attach an electrical cable to carry the quantity level signal. The direct quantity indicator may include a dial directly mounted on the accumulator. The remote/direct quantity indicators may include, for example, one of the following three combinations: 1) a dial directly on the accumulator and a remote dial at the end of a flexible cable; 2) an RVDT output and a dial directly on the accumulator; and 3) an RVDT output on an accumulator, a remote dial at the end of a flexible cable and a dial directly on the accumulator.

Abstract: A method for removing particulates from a fluid, the method including the steps of: producing a flow of the fluid down an outer rotor of a centrifuge; and imparting centrifugal force on the fluid in a direction orthogonal to a direction of the flow of the fluid to capture the particulates from the fluid.

Abstract: An apparatus for determining the fluid level of a container, such as an accumulator, may include both a remote quantity indicator and a direct quantity indicator. The remote quantity indicator may include a remote dial at the end of a flexible cable or an electrical signal receiver receiving an electrical signal from a rotary variable differential transformer (RVDT), such as a potentiometer. The RVDT type of indicator may include an electrical connector on the accumulator to attach an electrical cable to carry the quantity level signal. The direct quantity indicator may include a dial directly mounted on the accumulator. The remote/direct quantity indicators may include, for example, one of the following three combinations: 1) a dial directly on the accumulator and a remote dial at the end of a flexible cable; 2) an RVDT output and a dial directly on the accumulator; and 3) an RVDT output on an accumulator, a remote dial at the end of a flexible cable and a dial directly on the accumulator.

Abstract: A centrifuge is employed to continuously remove particulates from a fluid. In one embodiment, the centrifuge removes small particles of soot from lubricating oil of diesel engines. The fluid is introduced into the centrifuge through a distribution rotor so that vortexes are not propagated in the fluid. Laminar flow of the fluid down the sides of the outer rotor may contribute to the soot-removal effectiveness of the centrifuge.

Abstract: An engine starting apparatus and method may allow for two methods of engine start where only one engine gearbox accessory pad exists off the aircraft engine. A gearbox lubricating apparatus may also be provided to lubricate the gearbox at altitude without added complexity. Two engine starting inputs (for example, one input for ground start and one input for in-flight engine start) are provided while avoiding complex gearbox designs. Clutches may also be used to prevent the starter gearbox from continuous operation (rotation) after the engine has started. Apparatus and methods are also provided for improving the air-fuel combustion of the hot-gas turbine start input (for in-flight engine start) to minimize the build-up of solid carbon (soot) in and around the combustor and turbine nozzle flow passages.

Abstract: An engine starting apparatus and method may allow for two methods of engine start where only one engine gearbox accessory pad exists off the aircraft engine. A gearbox lubricating apparatus may also be provided to lubricate the gearbox at altitude without added complexity. Two engine starting inputs (for example, one input for ground start and one input for in-flight engine start) are provided while avoiding complex gearbox designs. Clutches may also be used to prevent the starter gearbox from continuous operation (rotation) after the engine has started. Apparatus and methods are also provided for improving the air-fuel combustion of the hot-gas turbine start input (for in-flight engine start) to minimize the build-up of solid carbon (soot) in and around the combustor and turbine nozzle flow passages.

Abstract: An emergency power system may provide hydraulic and electrical power to an aircraft in the event of a failure of the aircraft's primary control power system. The system may be constructed as a ram air turbine in which a single ram air fan may drive both a hydraulic pump and an electrical generator. A unique gearbox may incorporate compound gearing to permit the pump and the generator to be driven at different speeds. Thus the pump and the generator may be driven at their respective optimum speeds. The pump and the generator may be detachably mounted on a gearbox that supports the ram air fan. The detachable mounting of the pump and generator may accommodate ease of maintenance of these items. The gearbox may be provided with a ground testing port through which rotational testing force may be introduced to a shaft that supports the ram air fan. This may permit ground level testing of the system. Ground level testing may reduce a need to perform periodic in-flight testing of the system.

Abstract: A vibration damping sleeve for a stator assembly having radial vibration isolator features at both ends is provided. At one end, the vibration damping sleeve comprises a groove for a damping element such as an annular gasket while a plurality of beams circumferentially disposed are at the other end. The plurality of beams may comprise mounting flanges for mounting the stator to a housing support.

Abstract: A centrifuge is employed to continuously remove particulates from a fluid. In one embodiment, the centrifuge removes small particles of soot from lubricating oil of diesel engines. The fluid is introduced into the centrifuge through a distribution rotor so that vortexes are not propagated in the fluid. Laminar flow of the fluid down the sides of the outer rotor may contribute to the soot-removal effectiveness of the centrifuge.

Abstract: An engine starting apparatus and method may allow for two methods of engine start where only one engine gearbox accessory pad exists off the aircraft engine. A gearbox lubricating apparatus may also be provided to lubricate the gearbox at altitude without added complexity. Two engine starting inputs (for example, one input for ground start and one input for in-flight engine start) are provided while avoiding complex gearbox designs. Clutches may also be used to prevent the starter gearbox from continuous operation (rotation) after the engine has started. Apparatus and methods are also provided for improving the air-fuel combustion of the hot-gas turbine start input (for in-flight engine start) to minimize the build-up of solid carbon (soot) in and around the combustor and turbine nozzle flow passages.

Abstract: A rotary remote visual liquid quantity indicator allows a user to remotely determine the amount of liquid in a container, such as an accumulator on an aircraft. A flexible rotary cable assembly may be coupled between a rotatable drum and a remote indicator having a rotatable cap, the rotatable drum responsive to axial motion of a sweeper within the accumulator. Changes in the fluid level of the accumulator may be translated into rotational motion of the rotatable drum, which, via the flexible rotary cable assembly, changes a reading on a remotely located indicator.

Abstract: A ram air turbine power system includes a ram air turbine having a turbine shaft, turbine blades for rotating the turbine shaft; and an electrical generator or other power source device driven by a power shaft, for providing power. The power shaft has a generally hollow tubular shape, and the turbine shaft extends coaxially within the power shaft. The ram air turbine power system also includes a gearbox housing a planetary gear train, where one end of the gear train is a planetary sun gear spline coupled to the power shaft and the other end of the gear train is a planetary ring gear spline coupled to the turbine shaft so that the rotating turbine shaft drives the power shaft through the gear train increasing the speed of the power shaft over the speed of the turbine shaft.

Abstract: A ram air turbine power system includes a ram air turbine having a turbine shaft, turbine blades for rotating the turbine shaft; and an electrical generator or other power source device driven by a power shaft, for providing power. The power shaft has a generally hollow tubular shape, and the turbine shaft extends coaxially within the power shaft. The ram air turbine power system also includes a gearbox housing a planetary gear train, where one end of the gear train is a planetary sun gear spline coupled to the power shaft and the other end of the gear train is a planetary ring gear spline coupled to the turbine shaft so that the rotating turbine shaft drives the power shaft through the gear train increasing the speed of the power shaft over the speed of the turbine shaft.

Abstract: A ram air turbine system provides liquid cooling of its generator by employing a closed loop liquid cooling line originating from a pump in the gearbox of the system. In the preferred embodiment the pump may be a pitot pump to which gearbox lubricating oil may be channeled along a trough that is located in the gearbox. At least a portion of the trough is immersed in the oil which travels along the trough toward the pump in response to turbine shaft rotation. The oil is directed into a cooling jacket which is integral to the generator and then to a heat exchanger exposed to airflow. The oil is then returned to the gearbox.

Abstract: A ram air turbine power system includes a ram air turbine having a turbine shaft, turbine blades for rotating the turbine shaft; and an electrical generator or other power source device driven by a power shaft, for providing power. The power shaft has a generally hollow tubular shape, and the turbine shaft extends coaxially within the power shaft. The ram air turbine power system also includes a gearbox housing a planetary gear train, where one end of the gear train is a planetary sun gear spline coupled to the power shaft and the other end of the gear train is a planetary ring gear spline coupled to the turbine shaft so that the rotating turbine shaft drives the power shaft through the gear train increasing the speed of the power shaft over the speed of the turbine shaft.

Abstract: A ram air turbine system provides liquid cooling of its generator by employing a closed loop liquid cooling line originating from a pump in the gearbox of the system. In the preferred embodiment the pump may be a pitot pump to which gearbox lubricating oil may be channeled along a trough that is located in the gearbox. At least a portion of the trough is immersed in the oil which travels along the trough toward the pump in response to turbine shaft rotation. The oil is directed into a cooling jacket which is integral to the generator and then to a heat exchanger exposed to airflow. The oil is then returned to the gearbox.

Abstract: The heating apparatus and method for the nose fairing of a rotating blade assembly has an electrical generator connected to a heating element attached to the interior of the forward end of the nose fairing. The electrical generator has a rotor with conductor windings attached to the aft end of the rotating blade assembly hub housing. The stator of the electrical generator is attached opposite the rotor on the support structure for the hub housing with stator magnets spaced from and opposite the rotor windings. When the hub housing is rotated by for example airflow through the blades of the rotating blade assembly the rotor moves relative to the stator thereby creating an induced current in the windings. This converts the rotational energy to electrical energy to power the heater to heat the nose fairing to inhibit the formation of ice thereon.

Abstract: The heating apparatus and method for the nose fairing of a rotating blade assembly has an electrical generator connected to a heating element attached to the interior of the forward end of the nose fairing. The electrical generator has a rotor with conductor windings attached to the aft end of the rotating blade assembly hub housing. The stator of the electrical generator is attached opposite the rotor on the support structure for the hub housing with stator magnets spaced from and opposite the rotor windings. When the hub housing is rotated by for example airflow through the blades of the rotating blade assembly the rotor moves relative to the stator thereby creating an induced current in the windings. This converts the rotational energy to electrical energy to power the heater to heat the nose fairing to inhibit the formation of ice thereon.

Abstract: A follower spring for a foil thrust bearing includes a plate and a plurality of spring tabs extending from the plate. The spring tabs are elongated and offset at angles between approximately 45 degrees and approximately 75 degrees. The spring tabs can be arranged in pairs, with each pair defining a preload force center. The preload force centers can be located midway between a radial width of the plate and equally spaced apart about the plate in a circumferential direction.