Abstract: A propulsive assembly for an aircraft with an engine system with a core in a casing and having a combustion chamber and a turbine with blades, a supply line supplying dihydrogen, an injector manifold equipped with injectors which dip into the combustion chamber, and a distribution network with several bypass lines distributed around the casing, a rear manifold connected to the supply line and to the bypass lines and a front manifold connected to the bypass lines and to the injector manifold, in which the rear manifold is at the rear of the turbine and the front manifold is at the front of the turbine.

Abstract: An aircraft with at least one engine system, at least one zone for ejection of debris originating from the engine system and at least one fluid supply circuit. The latter comprises a shutter configured to occupy open and closed states, at least one return element configured to push the shutter to the closed state and at least one control positioned at least partially in the ejection zone and configured to hold the shutter in the open state against the return element. When the control is broken in the case of an accident, it no longer holds the shutter, which switches automatically to the closed state.

Abstract: A propulsive assembly for an aircraft with an engine system with a core in a casing and having a combustion chamber and a turbine with blades, a supply line supplying dihydrogen, an injector manifold equipped with injectors which dip into the combustion chamber, and a distribution network with several bypass lines distributed around the casing, a rear manifold connected to the supply line and to the bypass lines and a front manifold connected to the bypass lines and to the injector manifold, in which the rear manifold is at the rear of the turbine and the front manifold is at the front of the turbine.