COMBINED NUCLEAR AFTERBURNER AIRCRAFT ENGINE Russian patent published in 2010 - IPC F02K7/16 F02C1/05 

FIELD: engines and pumps.

SUBSTANCE: combined nuclear aircraft engine comprises two-stage gas turbine engine with inner and outer shafts, HP and LP compressors, combustion chamber with fuel line running from fuel pump connected thereto, turbine with cooling system and jet nozzle with taper fairing inside it. Stirling engine is fitted in engine inner shaft and comprises at least one work cylinder arranged downstream the turbine and at least one expansion cylinder mounted downstream the work cylinder. Ahead of work cylinder heat exchanger is mounted communicated by circulation pipelines with nuclear reactor. Every expansion cylinder has a casing to make, together with said cylinder, a cooling chamber with its inlet communicated with air feed branch pipe outlet. Air feed branch pipe inlet communicates, via flow rate controller, with a chamber arranged between LH and HP compressors. Cooling chamber outlet communicates with the chamber downstream the Stirling engine. Afterburner chamber is arranged between Stirling engine and supersonic jet nozzle to accommodate afterburner heat exchanger communicated with circulation pipelines, one of them accommodating circulation pump with afterburner chamber. Supersonic adjustable jet nozzle can vary critical section area. Aforesaid taper fairing is arranged inside jet nozzle subsonic section.

EFFECT: higher efficiency.

2 cl, 4 dwg