The invention relates to a container (200) for a heat storage and restitution system, comprising a vessel in which a gas is circulating in order to be cooled or heated. The vessel is limited by a first jacket formed from concrete (203) surrounded by a thermally insulating layer (206), which is itself surrounded by a steel shell (204). The vessel comprises at least two modules (210), each comprising a double wall formed from concrete and a perforated base (205) limiting at least two volumes (217 and 216) which are each capable of containing a fixed bed of particles of a material for storage and restitution of heat (207). The modules are disposed one above the other in a centered manner such that the double wall formed from concrete forms the first jacket formed from concrete (203) and a second jacket formed from concrete (215).

An aircraft engine according to an example of the present disclosure includes, among other things, a high pressure turbine having a blade, an engine casing disposed about the blade, a shield disposed around the casing adjacent to the blade and creating an area between the shield and the casing, and a gate disposed along the shield. The gate is rotatable about the engine casing between an opened position and a closed position for selectively controlling entry of cooling air into the area. A method of cooling an engine is also disclosed.

An assembly is provided for an aircraft propulsion system. This assembly includes a compressor section, a combustor section, a turbine section, a flowpath, a tail cone structure and a ventilation system. The flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath. The tail cone structure is arranged at the exhaust from the flowpath. The ventilation system is configured to bleed compressed air from the flowpath along the compressor section to provide ventilation air. The ventilation system is configured to direct the ventilation air into an internal volume in the tail cone structure.

An electric power system of a moving object includes a gas turbine engine including a compressor and a rotating electric machine connected to the gas turbine engine, a first bleed air flow path configured to introduce bleed air obtained by taking out a part of air compressed by the compressor into the rotating electric machine, and a second bleed air flow path configured to guide the bleed air introduced into the rotating electric machine to a component requiring cooling of the turbine engine.