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

FIELD: engines and pumps.

SUBSTANCE: nuclear turboprop gas turbine engine includes nuclear reactor, propeller, engine housing, 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 consists of low and high pressure sections. Turbine consists of high, intermediate and low pressure sections. Rotor of low pressure turbine is connected by means of inner shaft to propeller. Rotor of intermediate pressure turbine is connected by means of intermediate shaft to rotor of low pressure compressor. High pressure turbine rotor is connected through outer shaft to rotor of high pressure compressor. Radial partitions are installed between high and intermediate pressure turbines and between intermediate and low pressure turbines. Outside the engine housing there installed is heat exchanger-heater, the first and the second additional heat exchangers connected via recirculating pipelines to nuclear reactor and inlet and outlet air pipelines to cavities after compressor and before high pressure turbine, after high pressure turbine and before intermediate pressure turbine, after intermediate pressure turbine and before low pressure turbine.

EFFECT: higher engine acceleration and reliability.

5 cl, 5 dwg