Patent ID: 8403629

Claim:
A stator for installation in a rear section of a jet engine, the stator comprising a plurality of hollow guide vanes which extend in a radial direction of the stator and between them define ducts for leading a gas, a first side of the stator in its axial direction defining an inlet for the gas, a second side, opposite the first side, defining an outlet for the gas, and a radially outer ring to which the guide vanes are connected, the outer ring defining an inner duct for a core flow and a outer duct for a fan flow, wherein the guide vanes have such a shape that together they at least substantially cover the gas inlet viewed in the axial direction of the stator from the outlet side thereof, wherein each of the guide vanes comprises an inlet section, an outlet section and an intermediate section located between the inlet section and the outlet section, the intermediate section extending in a direction with a component in the circumferential direction of the stator, the intermediate section being of a length sufficient to at least substantially cover a space between two adjacent vanes, the guide vanes each comprise a radially outer opening connected to the outer duct and leading into an interior of the guide vane and at least one outlet opening from the interior of the guide vane to a side of the guide vane facing the outlet side of the stator, the guide vanes are arranged to lead a coolant from the outer duct into the interior of the guide vane through the radially outer opening and out of the interior of the guide vane through the at least one outlet opening, and a mechanical load is transmitted by the stator between the outer ring and an inner hearing.