Abstract: An inflatable evacuation device to simultaneously evacuate from both an overwing aircraft exit and an aircraft exit aft of the trailing edge of the aircraft wing.

Abstract: A foil thrust bearing having an underspring formed from a uniform thickness sheet wherein the underspring includes a plurality of arcuate tabs extending toward the thrust disk in the direction of rotation of the thrust runner.

Abstract: In a gas turbine engine compressor power unit fuel is supplied at an essentially constant pressure to a fuel nozzle for injection into the combustion liner of the power unit's combustor. Nozzle fuel flow is modulated solely by bleeding off combustor supply air to vary the internal liner pressure, thereby altering the fuel pressure drop across the nozzle.

Abstract: A heat exchanger of the type characterized by a plurality of preassembled heat exchanger tubes separated by cooling fins. Each tube is formed from two identical U-shaped members having a folded and unfolded end. The unfolded end of each is slid into the fold end of the other. The secondary of cool air flow path is defined by a pair of formed header bars alternated with the tubes. Side plates and manifolds are added to complete the heat exchanger.

Abstract: A turbocharger having a variable nozzle vane assembly to be used in association with an engine. A plurality of pivotable vanes are mounted between the turbocharger backplate and unison ring on one side and an annular side wall, independent of the turbine housing on the other. Each vane includes a drive pin which pivots the vane in response to rotational movement of the unison ring.

Abstract: Method and apparatus for compression of elastic fluids such as air in a rotary continuous flow process particularly of interest in the turbomachinery field. Resulting structure has an envelope or outer diameter favorably comparable with axial flow compressors and a static pressure ratio, cost, and resistance to FOD comparable to centrifugal compressors. Jet propulsion engine apparatus incorporating such a compressor is also presented.

Abstract: A diesel engine exhaust particulate trap and regeneration system for trapping of particulates in the engine exhaust gases and periodic burning thereof. Collected particulates in the trap are burned utilizing a burner means immediately upstream of the trap. An air and fuel supply system are associated with the burner which controls the combustion temperature within the burner in order to completely and efficiently burn the particulates.

Abstract: An arrangement for supplying coolant flow to turbine blades in a gas turbine engine is disclosed which utilizes a preswirl assembly to impart a tangential velocity to the coolant flow substantially greater than the tangential velocity of the rotor at the point at which the air is supplied to the rotor. The overswirled air is injected radially inwardly into an internal passage contained in the rotor, and the coolant flow continues to be an overswirled condition within the internal passageway. The amount of overswirl imparted to the coolant flow is such that the tangential velocity of the coolant flow is greater than the tangential velocity of the blades at the location on the blades the coolant flow is supplied to the blades for blade cooling, thereby resulting in substantially improved efficiency in the cooling system.

Abstract: An inertial coupling is provided for substantially preventing rotational speed variations of a free power turbine in a multiple shaft gas turbine engine in response to a transient load condition. The inertial coupling comprises a gear assembly having first and second rotatable components driven respectively by the free power turbine and by the gas generator section of the gas turbine engine to cooperatively drive a free-wheeling inertial mass. The inertial mass is rotated at a constant speed during steady-state engine operation and provides sufficient rotational inertia during a transient load condition to couple the free power turbine temporarily to the gas generator section to maintain free power turbine speed substantially constant during adjustment of an engine fuel control to accommodate the changed engine load.

Abstract: Radiant heat resistant fluid-distendable structure and methods for making same.

Abstract: A bleed flow modulator is used in conjunction with pressure regulating valves regulating bleed air pressure from each engine to a common manifold. The bleed flow modulator monitors the pressure drop across a heat exchanger, which pressure drop is proportional to flow rate of bleed air through the heat exchanger. By providing a limited authority negative feedback signal to the pressure regulating valve from the bleed flow modulator, flow rate of bleed air from each engine to the common manifold is kept near a desired uniform value, thereby achieving balanced flow extraction of bleed air from the aircraft engines.

Abstract: A foil thrust bearing having an underspring with alternating upper ridges and lower ridges.

Abstract: A two pole permanent magnet rotor utilizes a single cylindrical two pole permanet magnet mounted between two end pieces and surrounded by a retaining hoop. The cylindrical two pole permanent magnet, which is made of high energy product material, is "straight through" diametrically magnetized to provide a sinusoidal air gap flux distribution which eliminates losses due to harmonics. The cylindrical two pole permanent magnet may be made of a plurality of smaller magnet blocks which are stacked and machined to form a cylindrical configuration.

Abstract: An environmental control system having an ozone decomposition catalyst coating in the hot pass side of the primary heat exchanger. The environmental control system includes primary and secondary heat exchangers as well as a rotary compressor and a rotary turbine expander. The environmental control system is used in aircraft for providing conditioned air to the habitable space of the aircraft for life support purposes.

Abstract: To prevent surge in a compressor, the flow therethrough is automatically altered when the static pressure differential taken laterally across one of its diffuser vanes approaches a magnitude indicative of a surge condition.

Abstract: A dual alloy radial turbine rotor with high tensile strength hub material exposed in the saddle regions between the blades to prevent fatigue that causes cracks in the saddle regions is manufactured by producing the hub with additional material at the outer portions of a frustoconical rear portion of the hub. After diffusion bonding of the outer surface of the hub to the mating inner surface of the blade rim, portions of the blade rim in the saddle regions are machined away to produce finished saddle configurations with the high tensile strength hub material exposed.

Abstract: A turbocharger having a variable nozzle vane assembly to be used in association with an engine. A nozzle ring having a plurality of rotatable vanes mounted thereto defining an annular passageway within the turbine housing through which exhaust gas passes upstream of a turbine. Included is a means for rotating the plurality of vanes and a means for preventing binding of the components during thermal cycling.

Abstract: An electrically responsive turbocharger control for a turbocharged internal combustion engine includes an electrically operated control device selectively energizable to engage and lock in position the actuator for a wastegate control valve. This control device provides a manner of overriding the normal actuating forces acting in the wastegate control valve.

Abstract: A lightweight, compact turbocharger for small internal combustion engines having a reduced number of component parts for simplified construction, an improved bearing structure and a novel means of transmitting control pressure to the actuator.

Abstract: An improved rolling element jackscrew includes at least three planetary rollers interposed between an inner shaft and an outer nut, wherein one of the shaft and nut is formed with grooved threads of zero pitch and the other bears a spiral or pitched thread having a different number of threads per unit length. The different thread numbers on the nut and shaft are chosen to provide a pattern of nodal points at which the thread crests intersect, with the nodal points arranged along a plurality of equiangularly spaced axial contact lines corresponding with the number of rollers and defining positions of roller installation. The rollers each include axially spaced pairs of enlarged ribs defining axially spaced grooves meshing between the shaft and nut at the respective nodal points.