Abstract: In a compressor rotor assembly of an axial flow gas turbine engine, wherein the rotor disk has a circumferential blade retaining slot for receiving the root of each blade of a row of blades, a ladder seal is provided between the slot and the blade platforms to limit the leakage of working medium gases from the flow path and through the slot. During engine operation, the seal moves radially outwardly into sealing relation with the underside surface of each platform. At the same time, radially inwardly extending flanges of the seal move radially outwardly into sealing relation with the sidewalls of the disk slot.

Abstract: A rim seal for blocking the leakage of working medium gases between an array of rotor blades and a rotor disk is disclosed. Various construction details which provide positive contact between the seal and the disk are developed. The rim seal of the present invention is of the ladder-type having application to a disk adapted by a circumferential groove to receive the rotor blades.

Abstract: A case assembly for supporting stator vanes of a gas turbine engine is disclosed. Various construction details and techniques which enable support of the vanes across the flow path of the engine are discussed. The construction details and techniques which provide damping to the vanes and accommodate differential thermal expansion between the vanes and the case assembly are developed. The vane mounting system disclosed is built around the concept of enabling sliding friction between components of the case assembly to dampen vane vibrations.

Abstract: An object of the invention is to prevent the leakage of working medium gases across a rotor stage beneath the platforms of the rotor blades.A rotor assembly structure in which the concepts of the present invention are employable is disclosed. Techniques for blocking the leakage of working medium gases around a rotor stage beneath the platforms of the blades are discussed.