Turbo engine with cooler for cooling inlet air and turbine for expanding cryogenic fuel

An air-breathing turbojet engine for a hypersonic vehicle, comprising:

• a pump for pumping a cryogenic fuel;
• an inlet configured to compress inlet air by one or more shocks, thereby producing compressed inlet air;
• a cooler configured to cool the compressed inlet air using the cryogenic fuel, thereby producing cooled air;
• a turbo-compressor configured to receive cooled air from the cooler and to compress the air further, thereby producing compressed cooled air;
• a precooler between the inlet and the cooler, the precooler being configured to cool the compressed inlet air using compressed cooled air from the turbo-compressor;
• a combustor configured to receive compressed cooled air and a first portion of the cryogenic fuel for combustion therein, thereby producing combustion products;
• a first turbine configured to expand and be driven by combustion products from the combustor, and a second turbine configured to expand and be driven by a second portion of the cryogenic fuel, the first turbine and the second turbine being configured to drive the turbo-compressor via a shaft;
• and
• an afterburner configured to receive combustion products from the first turbine and the second portion of the cryogenic fuel from the second turbine for combustion therein.