LOW-SIZED GAS TURBINE ENGINE WITH HEAT RECOVERY Russian patent published in 2015 - IPC F02C7/10 

FIELD: engines and pumps.

SUBSTANCE: claimed engine comprises compressor with inlet device, gas-air recuperative heat exchanger, combustion chamber, compressor drive turbine and free turbine for driving the output consuming hardware arranged in one housing with gas collector. Heat exchanger is located downstream of the turbine and connected by air inlet with compressor outlet via air chamber and, by outlets, with inlets of combustion chamber fire tubes. Besides, it is connected by gas channels inlets with free turbine outlet and, by outputs, with engine gas collector. Combustion chamber is a tubular-circular design while heat exchanger is composed by modules. Combustion chamber fire tubes and heat exchanger modules are integrated into a single assy. Note here that heat exchanger modules and combustion chamber fire tubes are uniformly arranged in circle. Fire tubes are located between heat exchanger modules. Heat exchanger module air outlets are hydraulically communicated with combustion chamber fire tubes inlets via circular air manifold. Fire tubes inlets are connected to compressor drive turbine via individual gas ducts. Free turbine shaft is connected to output consuming hardware via reduction gearbox with output shaft.

EFFECT: higher efficiency, decreased overall dimensions and weight.

3 dwg