Abstract: A shrouded bladed-rotor for use as a rotor of an electrical generator incorporates a plurality of blades and an annular magnetically-permeable yoke concentric with an associated axis of revolution. An even-numbered plurality of permanent magnets are operatively coupled to an outer surface of the annular magnetically-permeable rotor yoke, the latter of which comprises either a shroud of the shrouded bladed-rotor or a ring of magnetically-permeable material encircling the shroud. The North-South axis of each permanent magnet is substantially radially oriented with respect to the axis of rotation, and North-South orientations of every pair of circumferentially-adjacent permanent magnets of the plurality of permanent magnets are opposite to one another. A non-magnetic magnet-retaining-ring encircling the plurality of permanent magnets has sufficient hoop strength to retain the plurality of permanent magnets on the annular magnetically-permeable rotor yoke during intended operation of the electrical generator.

Abstract: A shrouded bladed-rotor for use as a rotor of an electrical generator incorporates a plurality of blades and an annular magnetically-permeable yoke concentric with an associated axis of revolution. An even-numbered plurality of permanent magnets are operatively coupled to an outer surface of the annular magnetically-permeable rotor yoke, the latter of which comprises either a shroud of the shrouded bladed-rotor or a ring of magnetically-permeable material encircling the shroud. The North-South axis of each permanent magnet is substantially radially oriented with respect to the axis of rotation, and North-South orientations of every pair of circumferentially-adjacent permanent magnets of the plurality of permanent magnets are opposite to one another. A non-magnetic magnet-retaining-ring encircling the plurality of permanent magnets has sufficient hoop strength to retain the plurality of permanent magnets on the annular magnetically-permeable rotor yoke during intended operation of the electrical generator.

Abstract: An aircraft engine incorporates one or more externally-visible illuminators that are illuminated responsive to an activation signal. At least one of a quantity, a location, a pattern, a sequence, a color, or a color pattern of the one or more externally-visible illuminators, a control of at least one color of the one or more externally-visible illuminators, or a control of at least one intensity of the one or more externally-visible illuminators, is uniquely associated with the manufacturer of the aircraft engine, so as to provide for distinguishing the manufacturer of the aircraft engine while the aircraft engine is in operation in an aircraft.

Abstract: A turbocharger ball-bearing assembly incorporates a cageless set of ceramic bearing balls operating within outer and inner bearing raceways, wherein the outer bearing raceway is on the inside of a fractured outer race. The fractured outer race is located in a counterbore of a center body of a turbocharger. The center body, in cooperation with the ball-bearing assembly, provides for rotationally supporting, and axially restraining, a rotor shaft of the turbocharger. The outside diameter of the fractured outer bearing race is less than a corresponding inside diameter of the counterbore, and the center body provides for supplying lubricant to an isolation annulus therebetween, so as to provide fir squeeze-film damping the ball-bearing assembly within the counterbore.

Abstract: Liquid fuel from a rotary fluid trap is atomized by a sharp edge on an inside surface of an aft cavity of a bladed rotor of a gas turbine engine and directed into each of a plurality of associated hollow blades through corresponding blade inlet ducts that are in fluid communication with corresponding aft hollow interior portions of each blade. A radially-extending central rib within each blade partitions the hollow interior thereof into aft and forward hollow interior portions that are in fluid communication through an associated opening in the central rib and through a radially-extending gap between the central rib and the interior surface of the blade. A blade outlet duct provides for fluid communication between the forward hollow interior portion and a forward cavity of the bladed rotor, and a rotor outlet duct provides for discharging the fuel from a radially-inboard portion of the forward cavity.

Abstract: A control schedule incorporating a relationship between corrected torque and inlet pressure is selected or determined responsive to a power-level command representative of a level of power to be transmitted to a controllable load by a single-spool turboshaft engine. At least a substantial portion of the control schedule provides for a flat-rated power level by the single-spool turboshaft engine substantially independent of associated inlet air pressure and inlet air temperature, and for at least one selectable mode of operation, the control schedule provides for minimizing or nearly minimizing a measure of fuel consumption, and for at least one other selectable mode of operation, the control schedule provides for operation at a substantially fixed level of rotational speed.

Abstract: A rotor system for a rocket engine comprises a first hollow shaft portion and a surrounding annular duct. The interior of the first hollow shaft portion is adapted to receive a first propellant component, and is in fluid communication with a first rotary orifice. The annular duct is adapted to receive a second propellant component, and is in fluid communication with a second rotary orifice located proximate to the first rotary orifice. The rotor system further comprises a third rotary orifice operatively connected to second hollow shaft portion and in fluid communication with the interior of the first hollow shaft portion for discharging a second portion of the first propellant component at second location. The rotary orifices are operatively connected to respective rotary pressure traps that isolate the pressure at the respective rotary orifices from the respective inlet pressures of the respective propellant components.

Abstract: A rocket engine comprises first and second rotary injectors for injecting respective fuel and oxidizer propellant components into a first combustion chamber, and the effluent therefrom drives a turbine that rotates the rotary injectors. The mixture within the first combustion chamber is preferably fuel-rich so as to reduce the associated combustion temperature, and the fuel-rich effluent mixes in a second combustion chamber with additional oxidizer injected by a third rotary injector so as to generate a high temperature effluent suitable for propulsion. The rotary injectors are adapted so as to isolate the low pressure propellant supply from the relatively high pressures in the respective combustion chambers.

Abstract: A fuel lubricated anti-friction bearing comprises an inner race for an anti-friction bearing having a plurality of radially opening apertures communicating with a fuel supply, a rotatable outer race, and a plurality of anti-friction rollers between the inner and outer races, rotation of the outer race effecting rotation of the rollers and pumping of fuel radially outwardly through the apertures in the inner race of the rollers.

Abstract: A multi-spool turbofan engine has a high pressure spool that operates at high idle RPM so as to power accessories and minimize acceleration time from idle to full rated RPM without producing high idle thrust which compromises the landing maneuver and ground operation.

Abstract: An aft fan gas turbine engine comprises a coaxially related compressor, compressor turbine, fan turbine, and aft fan. An annular fuel tank is disposed about the compressor and an annular combustion chamber is disposed between the compressor and turbine.

Abstract: A ring seal comprises an annular seal segment that is fixed against rotation but is axially movable relative to a fixed seal segment. The axially movable seal segment has substantially equal oppositely facing exposed radial surfaces whereby fluid pressure acting against the rotatable segment is substantially balanced in opposite axial directions.