Abstract: A hydraulic control slide valve and toy motion simulating apparatus for imparting motion to an operator controlled by the hydraulic control slide valve to proportionally direct hydraulic fluid from pitch, roll, and yaw fluid nozzles to respective pitch, roll, and yaw receiving chambers which are pivotably disposed with respect to the nozzles. The valve has a pivotable slider block which in turn has a pitch and roll nozzle to proportionally direct hydraulic fluid to respective nose up and nose down pitch receiving chambers and clockwise and counter-clockwise roll receiving chambers and a yaw nozzle to proportionally direct hydraulic fluid to right and left yaw receiving chambers. The valve has a drain means for directing hydraulic fluid that doesn't flow into the receiving chambers out of the hydraulic control valve.

Abstract: A toy motion simulating apparatus for imparting motion to an operator controlled by a hydraulic control valve to proportionally direct hydraulic fluid from pitch, roll, and yaw fluid nozzles to respective pitch, roll, and yaw receiving chambers which are pivotably disposed with respect to the nozzles. A pitch and roll nozzle to proportionally direct hydraulic fluid to respective nose up and nose down pitch receiving chambers and clockwise and counter-clockwise roll receiving chambers and a yaw nozzle to proportionally direct hydraulic fluid to right and left yaw receiving chambers. The valve has a drain means for directing hydraulic fluid that doesn't flow into the receiving chambers out of the hydraulic control valve.

Abstract: In accordance with the present invention, a pyrometer adapter is disclosed for providing the optical head of a pyrometer access to a target area in a gas turbine engine, where the pyrometer adapter is subjected to relative motion between a first mounting surface and a second mounting surface, the pyrometer adapter including an outer tube having a first end mounted to the first mounting surface of the gas turbine engine and a second end terminating in a flange, and a second tube positioned radially inward of and in concentric arrangement with the outer tube, wherein the second tube extends through an opening in the first mounting surface so that the second tube is mounted at its first end to the gas turbine engine at the second mounting surface adjacent the target area and the pyrometer optical head is attached to a second end of the second tube, where the second tube also includes a flange extending from a middle portion thereof which is attached to the flange of the outer tube to form a flexible diaphragm wh

Abstract: The discharge flow from a rotary vane pump is metered by directing a portion of the pump discharge back into the pump inlet area. A servo controlled actuator apportions the relative amounts of inlet fluid and returns fluid which enters the vane cavities. This arrangement allows for the use of a fixed cam which provides improved pump performance as compared to comparable movable cam pump designs.

Abstract: An arrangement for a main fuel pump, a backup fuel pump, a main hydraulic pump, and a backup hydraulic pump, typically for a as turbine engine in an aircraft, includes an isolated fuel and hydraulic fluid system and a backup pumping arrangement employing two mechanically-coupled gear-type reversible pump-motors and appropriate control valves.

Abstract: In accordance with the present invention, a fuel flow circuit comprises a source of fluid, a first means for pressurizing the combustible fluid and pumping the pressurized fluid along a first path leading to a combustion apparatus for an internal combustion engine. The first means for pressurizing further pumping the combustible fluid along a second path to a first fluid-driven actuator adaptable to control some aspect of the engine. The first means for pressurizing further pumping the combustible fluid along a third path to a second means for pressurizing the combustible fluid. The second means for pressurizing pumping the combustible fluid along a fourth path, including a first diverting means, to a second fluid-driven actuator adapted to control some aspect of the engine or exhaust nozzle.

Abstract: An arrangement for a main fuel pump, a backup fuel pump, a main hydraulic pump, and a backup hydraulic pump, typically for a gas turbine engine in an aircraft, includes an isolated fuel and hydraulic fluid system and a backup pumping arranngement employing two mechanically-coupled gear-type reversible pump-motors and appropriate control valves.

Abstract: A check valve apparatus is provided for use in connecting two fluid passageways, such as between which have multiple fluid passageways. The check valve manifolds and servovalves apparatus includes a poppet seal and a spring which engages and biases the poppet outward in sealing engagement with a portion of the wall surrounding the fluid passageway entrance and the entrance is effective for receiving an extension of the other fluid passage so that the extension engages and biases the poppet open. Mounted on the poppet is a means for sealing and retaining said poppet within the cavity which in the preferred mode is an elastomeric O ring restrainedly mounted within an annular channel circumscribing the poppet. One embodiment contemplates servovalve including a casing having extensions which comprise a filter.

Abstract: In one form of the present invention, a plurality of serovalves are connected to a common manifold. The manifold transmits fluid pressure from the servovalves to a modulator piston which controls the fluid pressure applied to a hydraulic actuator piston. The servovalves are designed such that, if the fluid pressure provided by any one of them to the manifold falls below a threshold, then the servovalve disconnects itself from the manifold, allowing control of the modulator piston to be assumed by the remaining, functioning servovalves. The present invention can be used in control surface actuators of short takeoff and landing (STOL) aircraft.

Abstract: In one form of the present invention, a plurality of serovalves are connected to a common manifold. The manifold transmits fluid pressure from the servovalves to a modulator piston which controls the fluid pressure applied to a hydraulic actuator piston. The servovalves are designed such that, if the fluid pressure provided by any one of them to the manifold falls below a threshold, then the servovalve disconnects itself from the manifold, allowing control of the modulator piston to be assumed by the remaining, functioning servovalves. The present invention can be used in control surface actuators of short takeoff and landing (STOL) aircraft.

Abstract: A shear-type, fail-fixed servovalve is disclosed which includes a piston whose piston head is movably disposed in one chamber of a multi-chamber housing. A piston rod is attached to the piston head and extends into the other chambers. Two passages extend through the piston rod and communicate with the chamber on opposite sides of the piston head. A pair of input orifices are located proximate each other at one end of the piston rod, each corresponding to one passage. An angularly movable jet pipe emits fluid directed at the input orifices. The jet pipe has a null angular position disposed at a predetermined offset angle with respect to the axis of the piston rod, and directs fluid towards the pair of orifices. Means responsive to a selectively variable control signal for changing the angular position of the jet pipe is provided which is effective to produce a magnified linear piston displacement by varying the relative amounts of fluid supplied to the input orifices.

Abstract: The servovalve includes a primary jet of fluid. A variable control signal is adapted to vary the angular position of the primary jet from its maximum recovery position. A first fluid path is adapted to supply fluid to a servopiston at a variable pressure determined at least in part by the control signal. A second fluid path is adapted to receive a predetermined portion of the primary jet fluid when the control signal reaches a predetermined value. The second fluid path terminates in the vicinity of the primary jet and is adapted to direct a secondary jet of fluid at the primary jet to deflect the primary jet toward the input orifice of the second fluid path. The resultant positive fluid feedback in the second fluid path causes the primary jet to latch in a first angular position relative to the maximum recovery position when the control signal reaches a predetermined value.

Abstract: A simplified fail-fixed electrohydraulic servovalve for operating with a source of fluid under pressure, and a piston translatably disposed within a bore. The piston has a rod side face area which is less than its head side face area and translates in a first direction for electrical input signals above a first predetermined percent of a maximum rated input signal. At a second percent of the rated input signal, determined by the ratio of the piston rod side face area to the piston head side face area, the piston position is fixed. For electrical input signals greater than the second percent of the rated input signal the piston translates in the second direction. Any input signal below the first percent causes the piston to be fixed in place.

Abstract: An integrated control system for a gas turbine engine is provided wherein the system includes fuel control means for metering the flow of fuel to the engine, position signal generating means for providing a position signal to control the fuel control means and biasing means for providing a signal to bias the position signal during a normal mode of operation. An interfacing means is provided to automatically limit the rate of change of the position signal in order to limit the rate at which the flow of fuel to the engine may be changed during a failed mode of operation when the biasing means is inoperative. A rate limiter means is also included within the control system to automatically limit the rate of change of the position signal in order to limit the rate at which the flow of fuel to the engine may be reduced during engine deceleration.

Abstract: An improved integrated control system for a gas turbine engine includes fuel control means for metering the flow of fuel to the engine in accordance with a fuel control position signal. A primary control means generates a primary fuel control position signal. A back-up control means generates a back-up fuel control position signal as a function of the actual engine speed in a primary mode and as a function of the power lever angle in a back-up mode. Transfer means is included to receive both the primary and back-up fuel control position signals and to provide only the primary signal to the fuel control means when the system in the primary mode and to provide only the back-up signal to the fuel control means when the system is in the back-up mode.

Abstract: A concentric-tube heat exchanger is provided which includes a first longitudinally extending annular flow passage adapted to provide a flow path for a first fluid flowing therein and a first plurality of annular heat transferring plates disposed consecutively in the axial direction in the annular flow passage. The plates extend radially across the annular passage and each have a first set of apertures extending axially through the plate. First means are provided for at least partially defining a second longitudinally extending flow passage for a second fluid. The second flow passage is disposed concentrically with the first annular flow passage and is in sufficient proximity thereto to permit a transfer of heat between the first and second fluids through said first plates in the radial direction.

Abstract: A gas turbine engine fuel delivery and control system is provided with means to recirculate all fuel in excess of fuel control requirements back to the aircraft fuel tank, thereby increasing the fuel pump heat sink and decreasing the pump temperature rise without the addition of valving other than that normally employed. A fuel/oil heat exchanger and associated circuitry is provided to maintain the hot engine oil in heat exchange relationship with the cool engine fuel. Where anti-icing of the fuel filter is required, means are provided to maintain the fuel temperature entering the filter at or above a minimum level to prevent freezing thereof. In one embodiment, a divider valve is provided to take all excess fuel from either upstream or downstream of the fuel filter and route it back to the tanks, the ratio of upstream to downstream extraction being a function of fuel pump discharge pressure.

Abstract: A gas turbine engine fuel delivery and control system is provided with means to recirculate all fuel in excess of fuel control requirements back to the aircraft fuel tank, thereby increasing the fuel pump heat sink and decreasing the pump temperature rise without the addition of valving other than that normally employed. A fuel/oil heat exchanger and associated circuitry is provided to maintain the hot engine oil in heat exchange relationship with the cool engine fuel. Where anti-icing of the fuel filter is required, means are provided to maintain the fuel temperature entering the filter at or above a minimum level to prevent freezing thereof. In one embodiment, a divider valve is provided to take all excess fuel from either upstream or downstream of the fuel filter and route it back to the tanks, the ratio of upstream to downstream extraction being a function of fuel pump discharge pressure.

Abstract: A fluid metering and flow dividing valve is provided which is particularly adapted for use in a fuel distribution system associated with a gas turbine engine and includes first and second variable area valves. Each valve is comprised of a movable shoe member and a stationary plate member cooperating in sliding frictional engagement to define a variable fluid flow area. A shaft interconnects each movable shoe member and is selectively translatable by actuating means responsive to signal means to effect movement of the movable shoe members to thereby vary the variable fluid flow areas.