The possibility of extending the range of operation of turbojet engine to hypersonic Mach number and its possible uses have been investigated. It is well known that addition or an afterburner extends the range of turbojet to Mach number of about 3. A further addition or a cooling system between ram intake and compressor can extend this range to Mach number of up to 6, depending upon the specific impulse required. A study of the choice of cooling systems for the precooled turbojet has been made. Liquid methane is used as the fuel and while passing through a heat exchanger it does some cooling. The thermodynamic cycle study and other considerations show that for the remaining part or the cooling load an aerothermopressor is advantageous as compared to a water heat exchanger.

Mordell, D. (Supervisor)