| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: combined nuclear boost aircraft engine includes two-spool gas turbine engine with internal and external shafts and low and high pressure compressors, combustion chamber, turbine with cooling system and convergent-divergent exhaust nozzle. After turbine, on internal engine shaft there installed is Stirling engine which includes at least one operating cylinder installed downstream the turbine, and at least one expansion cylinder installed downstream operating cylinder. Before operating cylinder there installed is heat exchanger connected via recirculation pipelines to nuclear reactor. Each expansion cylinder has a casing forming together with that cylinder a cooling cavity. Cooling cavity inlet is connected to outlet of air supply connection pipe the inlet whereof is connected via flow rate control and heat exchanger - cooler to cavity between low and high pressure compressors. Cooling cavity outlet is connected to cavity after Stirling engine. Between Stirling engine and convergent-divergent exhaust nozzle there is augmentor inside which there installed is augmentor heat exchanger connected via recirculation pipelines, in one of which there installed is recirculation pump, to nuclear reactor. ^ EFFECT: increasing efficiency with simultaneous decrease of its weight, cost and improvement of reliability. ^ 2 cl, 3 dwg |
