Study of performance of the aircraft gas turbine engine integrated with a gas dynamic laser

Аннотация

We consider a turbofan engine (TFE), where the turbine rotor blades of the low pressure turbine (LPT) are micro-Laval nozzles. We demonstrated the possibility of integrating the super jet turbine and a jet nozzle as a single binary system for the purpose of generation of powerful coherence radiation. We estimated the efficiency of the binary high pressure emitting system being a TFE part.