COMBINED AIRCRAFT ENGINE Russian patent published in 2009 - IPC F02K5/02 F02K7/16 

FIELD: engines and pumps.

SUBSTANCE: combined aircraft engine comprises two-stage gas turbine engine with inner and outer shafts and two-stage compressor, main combustion chamber whereto fuel line runs from fuel pump, turbine and jet nozzle with inner fairing. Stirling engine is fitted on gas turbine engine inner shaft behind the turbine. Right ahead of aforesaid engine, additional combustion chamber is arranged whereto additional fuel pipeline runs from additional fuel pump. Stirling engine comprises at least one working cylinder fitted behind additional combustion chamber, and at least one expansion cylinder mounted inside inner cowl. Every expansion cylinder gas casing to make with the former a cooling chamber. Cooling chamber inlet communicates, via channel between two shafts, with chamber arranged behind compressor first stage, while its outlet communicates with jet nozzle inner space.

EFFECT: higher efficiency and reliability, reduced weight and costs.

2 cl, 3 dwg