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

FIELD: engines and pumps.

SUBSTANCE: combined aircraft engine consists of two-spool gas turbine engine with external and internal shafts and two compressor spools, the main combustion chamber to which there connected is fuel pipeline from fuel pump, turbine and jet nozzle. After the turbine on internal engine shaft there installed is Stirling engine in front of which an additional combustion chamber is installed, to which an additional fuel pipeline is connected from the additional fuel pump. Stirling engine consists of at least one working cylinder installed after the additional combustion chamber streamwise, and at least one expansion cylinder installed after the working cylinder streamwise. Each expansion cylinder has a casing comprising together with that cylinder a cooling cavity; the cooling cavity inlet is connected to air intake pipe, and the cooling cavity outlet is connected to jet nozzle. All the expansion cylinders are installed partially or completely inside cone fairing of jet nozzle.

EFFECT: increasing efficiency of aircraft engine at decreasing its weight, cost and improving reliability.

4 cl, 3 dwg