An aircraft component is used for an aircraft gas-turbine engine. The aircraft component includes an annular part, a flange, and a boss. The annular part has an outer circumferential surface. The flange is formed at one end portion of the annular part in an axial direction. The boss projects from the outer circumferential surface of the annular part to the radial direction. On a section cut along an axial direction of the annular part, the outer circumferential surface of the annular part between the flange and the boss has a taper part that is formed into a tapered shape in which plate thickness becomes thicker from the flange toward the boss.

An aircraft component is used for an aircraft gas-turbine engine. The aircraft component includes an annular part, a flange, and a boss. The annular part has an outer circumferential surface. The flange is formed at one end portion of the annular part in an axial direction. The boss projects from the outer circumferential surface of the annular part to the radial direction. On a section cut along an axial direction of the annular part, the outer circumferential surface of the annular part between the flange and the boss has a taper part that is formed into a tapered shape in which plate thickness becomes thicker from the flange toward the boss.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

A dual flow turbine engine includes at least one lubricant tank located in an annular space of the turbine engine body and at least one hatch which is provided on an external cowling of a nacelle, for filling the tank. The tank is configured to be filled, by means of a removable tubular pipe inserted from the hatch into the tank, through canisters. One of the canisters includes a first interface through which the pipe is configured to pass, and another canister includes a second interface for connecting the pipe to the tank.

A dual flow turbine engine includes at least one lubricant tank located in an annular space of the turbine engine body and at least one hatch which is provided on an external cowling of a nacelle, for filling the tank. The tank is configured to be filled, by means of a removable tubular pipe inserted from the hatch into the tank, through canisters. One of the canisters includes a first interface through which the pipe is configured to pass, and another canister includes a second interface for connecting the pipe to the tank.

A propulsion system is provided and includes a solid hydride storage unit from which gaseous hydrogen fuel is drawn, an engine comprising a combustion chamber and a piping system to draw the gaseous hydrogen fuel from the solid hydride storage unit, the piping system being interposed between the solid hydride storage unit and the combustion chamber. The combustion chamber is receptive of the gaseous hydrogen fuel drawn from the solid hydride storage unit by the piping system and is configured to combust the gaseous hydrogen fuel to drive an operation of the engine.

A vehicle includes a body, at least one propulsion system including an electric component, a strut extending between the body and the at least one propulsion system, and a cooling system operably coupled to the electric component of the at least one propulsion system. A portion of the cooling system is arranged within the strut.

An outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud including: an annular downstream portion provided with a shroud opening passing through an annular downstream edge of the shroud; a connecting member (50) attached to the annular downstream portion, and intended to attach an arm that passes through a secondary flow path; an air-sealing and fire-resistance device including: a portion including: a pad arranged in a hollow annular area of the annular downstream edge of the shroud; a blade protruding from the pad and clamped between a circumferential end and the radially outer end of the arm, a leaf spring (pressing the pad into the hollow annular area.

An outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud including: an annular downstream portion provided with a shroud opening passing through an annular downstream edge of the shroud; a connecting member (50) attached to the annular downstream portion, and intended to attach an arm that passes through a secondary flow path; an air-sealing and fire-resistance device including: a portion including: a pad arranged in a hollow annular area of the annular downstream edge of the shroud; a blade protruding from the pad and clamped between a circumferential end and the radially outer end of the arm, a leaf spring (pressing the pad into the hollow annular area.