Turbine engine including a continuous wave detonation chamber and cooling bypass flow and aircraft provided with such a turbine engine

A turbomachine comprising:

• a compressor (3) configured to generate a compressed air flow from an incoming air flow (E);
• a chamber (4), in which a first portion of said compressed air flow flows through at least one additional compressor (11) to form a first compressed air flow (F1), and a remainder of said compressed air flow forms a second compressed air flow (F2) that flows around said at least one additional compressor, said chamber (4) comprising a continuous detonation wave engine (6), fitted with at least one annular detonation chamber (7) and associated means (8, 9) to generate continuous production of hot gases from an explosive mixture of a fuel and-said first compressed air flow, wherein said fuel is injected into said at least one annular detonation chamber independent of said first compressed air flow;
• auxiliary means (10) for mixing the hot gases (f3) emanating from said at least one annular detonation chamber (7) with said second compressed air flow (F2) to generate a mixed gas flow;
• at least one additional annular detonation chamber (7) arranged in a concentric manner in relation to at least one annular detonation chamber, and in relation to a central axis (2) of the turbomachine (1);
• and
• a turbine (5) driven in rotation by said mixed gas flow, and wherein said turbine drives said compressor (3).