NUCLEAR TURBOPROP GAS TURBINE ENGINE Russian patent published in 2011 - IPC F02K3/00 F02C1/05 

FIELD: engines and pumps.

SUBSTANCE: nuclear turboprop gas turbine engine includes nuclear reactor, propeller, air intake, compressor, combustion chamber, turbine, heat exchanger-heater and jet nozzle. Engine is made as per three-shaft scheme and consists of outer, intermediate and inner shafts. Compressor includes low and high pressure spools, and turbine includes high, intermediate and low pressure spools. Rotor of low pressure turbine is connected through inner shaft to propeller. Rotor of intermediate pressure turbine is connected through intermediate shaft to rotor of low pressure compressor. High pressure turbine rotor is connected through outer shaft to rotor of high pressure compressor. The first and the second additional heat exchangers connected through recirculation pipelines to nuclear reactor are installed respectively between turbines of high and intermediate pressure and between turbines of intermediate and low pressure.

EFFECT: higher engine acceleration and reliability.

4 cl, 4 dwg