NUCLEAR GAS-TURBINE AVIATION ENGINE Russian patent published in 2009 - IPC F02C1/05 F02G1/43 

FIELD: engines and pumps.

SUBSTANCE: nuclear gas-turbine aviation engine comprises the first and second circuits, air intake, external and internal shafts with fan installed on internal shaft and compressor installed on external shaft, at least one turbine impeller installed on external shaft, and also jet nozzle. Combustion chamber is located between compressor and turbine. Stirling engine is installed downstream turbine, and the engine is connected kinematically to internal shaft and connected by coolant circulation pipelines to nuclear reactor. Upstream combustion chamber and in the second circuit heat exchangers are installed, which are connected by recirculation pipelines to nuclear reactor. Stirling engine is made of two groups of cylinders: working and piston ones, at that working cylinders are located in the first circuit, and expanding cylinders are located in the second one. Air nozzles are connected to Stirling engine. Ends of air nozzles exit to atmosphere or are connected to air intake or outlet from the first stages of compressor.

EFFECT: increased efficiency factor and higher reliability of engine.

6 cl, 6 dwg