AERONAUTICAL COMBUSTION MACHINE COMPRISING A RESERVE OF PRESSURIZED FLUID FOR STARTING A CLOSED-CYCLE ENGINE

摘要

The invention relates to an aeronautical combustion machine (100) comprising a closed-cycle combustion engine (3) and at least one turbocompressor (4, 5, 14). According to the invention, the combustion machine (100) comprises an auxiliary starting device (120) comprising a reserve (1) of fluid kept at a pressure higher than that of the external ambient air, an auxiliary compressor (10) and an auxiliary turbine (11) connected by an auxiliary shaft (12) to the auxiliary compressor (10). The auxiliary starting device (120) is configured such that a release of pressurized fluid from the reserve (1) into the auxiliary turbine (11) causes pressurized air to be introduced into the main combustion chamber (30) from the auxiliary compressor (10).