Abstract: An apparatus for cooling components of an airplane engine at least partially operated by a cryogenically stored propellant via cooling air includes an air supply line for supplying the cooling air from an outside environment. A heat exchanger exchanges the cooling air with the propellant to precool the cooling air and includes a condenser having an in-flow and an out-flow side connected to the air supply line for precooling the cooling air. A pump is coupled to a cooling air line for conveying the precooled air in a liquid or vapor state to the components to be cooled wherein the cryogenically stored propellant acts upon the condenser. A propellant tank is connected to the in-flow side of the condenser and stores the cryogenically stored propellant, wherein the out-flow side of the condenser is connected to at least one combustion system of the airplane engine.

Abstract: A stationary centerbody includes vaulted areas displaced substantially by 180.degree. axially as well as along the circumference with respect to one another on its largest relative diameter. The vaulted areas, while enclosing a shut-off surface which is diagonal on the circumference side with respect to the end of an engine shroud forming a casing lip, encloses an axially spaced circumferential surface which is shut off in the manner of an annular slide valve from the end of the shroud.

Abstract: With surface sections vaulted with respect to the valve centerline the valve mates with a stationary companion surface on an annular casing lip to optionally shut off or expose the engine by having vaulted surface sections which are arranged at an axial distance an angularly offset over the circumference by essentially 180.degree. with the valve centerline, forming its largest relative diameter; where the vaulted surface sections form a valve of axially and circumferentially three-dimensionally displaced drop or mushroom shape.