FIELD: engines and pumps.
SUBSTANCE: invention relates to a starter device of an engine rocket turbo pump (1) in an aircraft comprising a propulsion turbine engine of the aircraft and a rocket motor, comprising pneumatic supply start of turbine (1a) of the turbopump by a compressed air injection circuit taken by means of fitting (4) on compressor stage (6a) of turbine engine (5) of the aircraft propeller upstream of the combustion chamber (7) of said turbine engine. It can be applied, in particular, for an aircraft such as an aerospace aircraft.
EFFECT: invention provides a reduction in the temperature acting on the turbopumps.
14 cl, 4 dwg
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