Turbomachine with detonation chamber and aircraft provided with such a turbomachine

The turbomachine (1) has a continuous detonation wave engine (6) provided with an annular detonation chamber (7), and a fuel injection system (8) and a priming unit (9) for continuous production of hot gas (F3) from a detonation mixture of fuel and air. A turbine (5) is rotatably driven by the hot gas, and drives a compressor (3). An ejector/mixer system (10) mixes the gas from the chamber with air flow (F2) before directing the gas toward the turbine. The chamber is arranged with another detonation chamber in a concentric manner relative to an axis (2) of the turbomachine.