Abstract: A small gas turbine generator set comprising a rotating group and combustor contained within a circumferential recuperator. The rotating group comprises an alternator rotor on a common shaft with a turbine wheel and compressor impeller, supported by double acting complaint foil thrust bearings and a radial compliant foil bearing. The circumferential recuperator consists of a plurality of apertured boundary foils having embossments for structurally spacing the foils apart, arranged to provide the flow channels, manifolds, and structure to permit the existence of differential pressure between each surface of the foil. The circumferential recuperator is unitarily constructed surrounding the rotating group and combustor wherein the inflowing air is heated by the recuperator before entering the combustor.

Abstract: A strobe lamp switching system includes first, second and third capacitors of different value for simultaneously storing energy from a DC power supply. The strobe lamp is connected across the power supply and periodically fired by energizing an ignition electrode. The number of capacitors are permitted to discharge through the strobe lamp determines the intensity of its light output. An intensity control energizes a pair of relay operated switches that complete discharge paths for the second and third capacitors. A diode parallels each of the relay operated switches so that the second and third capacitors are charged whenever the power supply is on. A discharge resistor is coupled across the power supply for discharging energy in all of the capacitors when the power supply is off.

Abstract: Improved combustor volume in turbine engines without an increased engine envelope is accomplished in an engine 10 have a radial compressor 12, an axial turbine 16, and a radial combustor 20 in which a generally radial flow path extends between a compressed air inlet 30 and a turbine nozzle 22 for gases of combustion produced by combusting fuel introduced through a fuel injector 34 with air introduced through the compressed air inlet 30.

Abstract: The fuel nozzles in the combustor of a gas turbine engine are concentrically disposed in two tiers about the circumference of the dome and are arranged in a triangular pattern with the air swirl orientation providing an increased intensity of combustion so as to enable a reduction in combustor size and weight while increasing temperature rise and the overall thrust-to-weight ratio of the engine.