TURBINE ENGINE INCLUDING A DETONATION CHAMBER AND AIRCRAFT PROVIDED WITH SUCH A TURBINE ENGINE

摘要

The invention relates to a turbine engine including a detonation chamber and an aircraft provided with such a turbine engine. The chamber (4) of the turbine engine (1) comprises a continuous detonation wave engine (6) provided with an annular detonation chamber (7) and associated means (8, 9) that can be used to generate a continuous production of hot gases from a detonation mixture of fuel and air. The continuous detonation wave engine (6) is arranged such as to form, from a flow of incoming air (E), a first flow (F1) which enters the detonation chamber (7) and which is used by the engine (6) and a second flow (F2) which bypasses the chamber. The turbine engine (1) also includes auxiliary means (10) for mixing the hot gases (F3) leaving the detonation chamber (7) with the second flow of air (F2) before directing same towards the turbine (5). A plurality of detonation chambers (7) are arranged concentrically to one another relative to the axis of the turbine engine.

主权项

1. Turbomachine of the type comprising at least, in the flow direction (12) of the gases, a compressor (3), a chamber (4) comprising means capable of generating hot gases from an air mixture originating from a captured air flow and from a fuel, and a turbine (5) which is driven in rotation by said hot gases and which drives said compressor (3), said chamber (4) comprising a continuous detonation wave engine (6), fitted with an annular detonation chamber (7) and associated means (8, 9) making it possible to generate continuous production of hot gases from an explosive fuel and air mixture, said continuous detonation wave engine (6) being arranged so as to form, from said captured air flow (E), a first flow (F1) which enters said detonation chamber (7) and which is used by said engine (6), and a second flow (F2) which bypasses said chamber, wherein said turbomachine (1) comprises, in addition:
auxiliary means (10) for mixing the hot gases (F3) emanating from the detonation chamber (7) with said second air flow (F2) before conducting them towards the turbine (5); and a plurality of detonation chambers (7) which are arranged in a concentric manner in relation to each other, relative to the axis (2) of the turbomachine (1), making it possible to create optimal operating conditions over a wide range of concentrations and to limit the shock at start-up.