Abstract: A hybrid ram air turbine assembly includes a turbine portion having a plurality of turbine blades connected to a turbine shaft via a hub. A pivot joint is connected to the turbine portion by a hydraulic pump and an electric generator. The hydraulic pump and the electric generator are in-line with each other, and the turbine shaft is connected to a generator input shaft via a first gear set.

Abstract: A hybrid ram air turbine assembly includes a turbine portion having a plurality of turbine blades connected to a turbine shaft via a hub. A pivot joint is connected to the turbine portion by a hydraulic pump and an electric generator. The hydraulic pump and the electric generator are in-line with each other, and the turbine shaft is connected to a generator input shaft via a first gear set.

Abstract: A system for providing alternating current (AC) power to an aircraft component includes a ram air turbine (RAT) configured to generate AC power. The system also includes an energy storage device configured to output direct current (DC) power. The system also includes an inverter configured to convert the DC power to the AC power. The system also includes a controller coupled to the RAT and the inverter and configured to cause the inverter to provide the AC power to the aircraft component, and to control the RAT to provide the AC power to the aircraft component in response to determining that the RAT can provide the AC power.

Abstract: A ram air turbine movable between a stowed position and a deployed position is provided including a rotatable hub assembly. A hub face is arranged at a first end of the rotatable hub assembly. The hub face has a non-planar configuration such that a limited portion of a surface area of the hub face is arranged within a plane oriented perpendicular to a direction of travel of an airflow upstream from the hub face when the ram air turbine is in a deployed position.

Abstract: A ram air turbine control valve includes a sleeve, a spool, and a return housing. The sleeve defines a first exit port disposed proximate a first end of the sleeve and defines a second exit port disposed between the first exit port and the first end. The spool is radially contained within the sleeve and is movable between a first position and a second position. The return housing is coupled to the first end of the sleeve and defines a cavity that receives a biasing member that engages the spool.

Abstract: A locking mechanism for a ram air turbine (RAT) includes a base clevis configured to mount to a housing and to have a base link clevis connector portion defining a plurality of base link clevis connector arms and a base link clevis having a base connector portion defining base connector arms that are configure to movably connect to the base link clevis connector arm. The locking mechanism also includes a pin operatively connecting the base connector portion to the base link clevis connector portion in a rotatable relationship and a spring positioned around the pin, wherein a first spring end abuts the base clevis and a second spring end abuts the base link clevis to bias the base link clevis to an unlocked position. A sleeve is positioned between the spring and the pin to maintain a wind diameter of the spring.

Abstract: A ram air turbine control valve includes a sleeve, a spool, and a return housing. The sleeve defines a first exit port disposed proximate a first end of the sleeve and defines a second exit port disposed between the first exit port and the first end. The spool is radially contained within the sleeve and is movable between a first position and a second position. The return housing is coupled to the first end of the sleeve and defines a cavity that receives a biasing member that engages the spool.

Abstract: In one aspect, a ram air turbine stall recovery system includes a ram air turbine, a hydraulic pump powered by the ram air turbine with the hydraulic pump having a pump inlet and a pump outlet, an electric generator powered by the ram air turbine, a bypass line that connects the pump outlet to the pump inlet, a bypass valve located on the bypass line between the pump outlet and the pump inlet; and a controller responsive to an input signal that indicates a potential stall condition of the ram air turbine. The controller causes the bypass valve to open to allow a hydraulic fluid to flow through the bypass line in order to reduce a pressure within the hydraulic pump.

Abstract: A locking mechanism for a ram air turbine (RAT) includes a base clevis configured to mount to a housing and to have a base link clevis connector portion defining a plurality of base link clevis connector arms and a base link clevis having a base connector portion defining base connector arms that are configure to movably connect to the base link clevis connector arm. The locking mechanism also includes a pin operatively connecting the base connector portion to the base link clevis connector portion in a rotatable relationship and a spring positioned around the pin, wherein a first spring end abuts the base clevis and a second spring end abuts the base link clevis to bias the base link clevis to an unlocked position. A sleeve is positioned between the spring and the pin to maintain a wind diameter of the spring.

Abstract: A ram air turbine movable between a stowed position and a deployed position is provided including a rotatable hub assembly. A hub face is arranged at a first end of the rotatable hub assembly. The hub face has a non-planar configuration such that a limited portion of a surface area of the hub face is arranged within a plane oriented perpendicular to a direction of travel of an airflow upstream from the hub face when the ram air turbine is in a deployed position.

Abstract: In one aspect, a ram air turbine stall recovery system includes a ram air turbine, a hydraulic pump powered by the ram air turbine with the hydraulic pump having a pump inlet and a pump outlet, an electric generator powered by the ram air turbine, a bypass line that connects the pump outlet to the pump inlet, a bypass valve located on the bypass line between the pump outlet and the pump inlet; and a controller responsive to an input signal that indicates a potential stall condition of the ram air turbine. The controller causes the bypass valve to open to allow a hydraulic fluid to flow through the bypass line in order to reduce a pressure within the hydraulic pump.

Abstract: A ram air turbine with a strut that is pivotable through a pivot plane about a pivot point on the strut from a generally horizontal rearward rest position to a generally vertical central operating position comprises at least one movable brace that extends between a stationary brace mounting point and a brace support point on the strut below the pivot point.

Abstract: An improved ram air turbine (RAT) prevents release of its turbine blades due an over-speed condition by detecting an over-speed condition with a trigger mechanism and rotating the blades to a fixed coarse pitch position with a release mechanism.

Abstract: A brake system for a ram air turbine (RAT) causes the RAT to slow or lock if the RAT achieves an over-speed condition with a centrifugal force operated trigger system that actuates a compression type brake pack to slow or lock the turbine hub.

Abstract: A ram air turbine (RAT) prevents release of its turbine blades due an over-speed condition by detecting an over-speed condition with a turbine hub-mounted centrifugally operated trigger mechanism and rotating the blades to a fixed coarse pitch position with a release mechanism that responds to the trigger mechanism.

Abstract: One or more formulations for treating psoriasis and other skin disorders characterized by redness, itching, flaking, scaling, and plaque-type growth. The formulation includes a carrier component, one or more active ingredient components, and a surfactant component. The carrier preferably includes an alcohol in substantially equal volume with isopropyl myristate. The active ingredient component preferably includes a superpotent or high-potency corticosteroid such as clobetasol propionate, an anti-flaking ingredient such as zinc pyrithione, or a combination of the two. It may also include an anti-fungal compound. The surfactant component preferably includes an alkyl sulfate such as sodium lauryl sulfate. The formulations made by applied topically either in spray form or as a direct-contact liquid.

Abstract: An undesirably long axial length of a ram air turbine may be reduced in a construction including a hub (110) mounted for rotation about a rotational axis (112), at least one turbine blade (114) rotatably mounted on the hub (110) for rotation between coarse and fine pitch positions about a blade pitch axis (116) which is different from the rotational axis (112) and a counterweight assembly (120) for each turbine blade (114) and mounted on the hub (110) for rotation between coarse and fine pitch positions about the blade pitch axis (116) in spaced relation to the rotational axis (114) and disposed when rotated about the rotational axis (112) to bias the turbine blade (114) towards its coarse pitch position. A limited lost motion connection (143, 144, 145, 146, 147, 148, 150) is located between the turbine blade (114) and the counterweight assembly (120).

Abstract: An improved RAM air turbine (30) for the generation of emergency power on an airplane is disclosed. The RAM air turbine has an operational range in which reduced power is produced by a power controller (40) at speeds at which stalling of the RAM air turbine would occur under the control of a governor (16) which adjusts the pitch of the blades (12) of the turbine in combination with a pressure regulator (150) controlling the output of pressurized hydraulic fluid from a variable displacement hydraulic pump (19).

Abstract: A drive system is provided between a ram air turbine (10) and at least a pair of accessory power units (38,40) of an aircraft, the ram air turbine being movable between stowed and deployed positions relative to the fuselage of the aircraft. The problems of providing a compact lightweight design which eliminates extraneous components in the airstream and a system which operates at optimum speeds are solved by the use of a drive shaft (28) extending between the ram air turbine and a first accessory power unit (38), such as a hydraulic pump, within the aircraft fuselage. First gears (30, 34) rotatably couple an outer end of the main drive shaft to the ram air turbine. Second gears (36,48) rotatably couple an inner end of the main drive shaft to the first accessory power unit. Third gears, in the form of a gear train (54), rotatably couple the first accessory power unit to a second accessory power unit (40), such as an electrical generator, within the aircraft fuselage.

Abstract: A dual function brake and manual drive actuating system for selectively holding a rotatable member of a drive train and manually driving the drive train. A support structure is provided, with a brake operatively associated between the support structure and the rotatable member for holding the member against rotation. A common release member is operatively associated with the brake. A fluid retracting mechanism operates against the common release member to selectively hold the brake in disengaged condition. A manual retracting mechanism also operates against the common release member to selectively hold the brake in disengaged condition. A manual drive is incorporated in the manual retracting mechanism for manually rotating the rotatable member when in the disengaged condtion.