FIELD: motors and pumps.;SUBSTANCE: invention relates to rocket-space and aircraft engineering and can be used in the creation of high-speed aircraft engines as their main propulsion system. Hypersonic turbojet engine contains a housing with an air intake and a diffuser, a shaft, compressor blades located on the shaft behind the diffuser, combustion chambers installed inside the housing parallel to the shaft, turbine blades placed on the shaft after the combustion chambers, a nozzle mounted on the housing behind the turbine blades. In the structure of the engine introduced thermionic layers from the material with a low electronic work function, applied respectively to the compressor blades, turbine blades and on internal surfaces installed inside the housing through electrically conductive gaskets of combustion chambers attached to the nozzle through the insulating spacer element – anode in the form of a conductive substrate with a layer of electrons on the surface facing the axis of the housing from a material with a low electronic work function, source of electricity, which is connected to the conductive substrate of the anode by its positive pole, and connected to the housing by a negative pole.;EFFECT: invention is aimed at expanding the range of flight speeds of a turbojet engine by using electronic cooling of heat-stressed engine components.;1 cl, 1 dwg
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