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, housing, air intake, compressor, combustion chamber, turbine the housing of which has conical shape which diverges streamwise, 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. 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. Additional heat exchangers are built in turbine housing so that they are partially arranged in turbine path and connected via supply air pipelines to cavity after high pressure compressor.

EFFECT: higher engine acceleration and reliability.

4 cl, 4 dwg