The Brayton cycle applied to gas turbines, what the compressor, combustor, turbine, and nozzle each actually do, why bypass ratio governs a turbofan's efficiency-versus-thrust trade-off, and the performance parameters engines are specified by.
Every gas-turbine jet engine runs the same four-step Brayton cycle — compress, add heat, expand through a turbine, exhaust — continuously rather than in closed batches the way a piston engine does, which is exactly why gas turbines deliver far higher power for their weight. This module walks the engine core component by component — compressor, combustor, turbine, nozzle — building on Module 5's thrust equation to show how bypass ratio is the single design parameter that positions a turbofan anywhere from propeller-like efficiency to turbojet-like speed.
By the end of this module you should be able to explain why turbine inlet temperature, not aerodynamics, has been the primary limit on jet engine performance for decades, and why thermal efficiency and propulsive efficiency respond to different design choices — the exact distinction this module's closing section on engine performance parameters is built around.