FIELD: engines and pumps.
SUBSTANCE: invention relates to turbojet engines of nuclear-powered aircraft. Nuclear jet turbine engine includes: nuclear reactor with liquid metal heat carrier, inlet device, compressor, two-section heating chamber, turbine, nozzle, thermal electric generators and/or thermionic converters, electric heating elements, pump and augmenter. Hot liquid metal from reactor core is used to transfer heat to air passing through the first section of heating chamber, and then to heat transfer to thermoelectric generators made in the form of plates. Cold side of plates is cooled by outboard air. Generated electric current is supplied to electric heating elements in the second section of the heating chamber. Air heated in the first and second sections of the heating chamber expands, drives the turbine, which is mechanically connected to the compressor, and generates a reactive thrust. Liquid metal is returned to reactor core by electromagnetic pump. Afterburner chamber uses liquid fuel and provides temporary increase in the speed of an airplane.
EFFECT: combination of higher safety and specific thrust of nuclear TJE.
6 cl, 2 dwg
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