Abstract: A shroudless turbine rotor blade of the type having a platform damper interface, is provided with at least one slot which extends from the aerofoil side of a platform flow boundary to a point in the root. The slot extends between opposing flanks of the blade so as to divide the platform and partially divide the root. The segregated root is made more flexible by the slot which provides for greater platform vibratory amplitudes for a given length of root. The increased platform motion provides for improved dampability when the blade vibrates. The slot also provides a pair of confronting platform surfaces which are urged into mutual contact by centrifugal load acting on the blade to create an additional damping interface.

Abstract: A gas turbine engine having a main casing, turbine blades and a segmented cylindrical liner surrounding the tips of the blades is provided with apparatus for compensating for different radial expansions between the blades and the liner. The apparatus comprises a shroud structure, such as a platform of an axially adjacent nozzle guide vane, and a slipper element extending radially from the shroud structure to the liner and coupling one to the other. The slipper element expands circumferentially more slowly than does the shroud structure. Thermal circumferential growth of the shroud structure causes a radial displacement of the liner segments relative to the shroud structure.

Abstract: A vane for a gas turbine engine comprising a hollow body externally of aerofoil form. The inner surface of the body is provided with confronting grooves, extending in a direction along the length of the aerofoil form, at a location intermediate the leading and trailing edges of the aerofoil form for receiving two inserts. The first insert comprises two perforated panels situated inside a trailing region of the aerofoil form and defining therewith one or more air passages between the insert and the wall of the body. The first insert has portions which engage in the grooves in the wall of the body, and is provided with confronting grooves extending in a direction along the length of the aerofoil form at a location intermediate the leading and trailing edges of the aerofoil form. The second insert comprises a first panel extending across the void in the body, and has edges which engage in the confronting grooves in the first insert.