Patent ID: 7775766

Claim:
A gas turbine engine comprising a rotatable rotor with rotor blades, which optionally have seal fins on radially outer blade tips of the rotor blades, and an abradable shroud lining arranged circumferentially around the blade tips such that the seal fins or the blade tips graze the abradable shroud lining, wherein: the abradable shroud lining comprises a carrier having a carrier surface, and an open-pored metal foam component having a back surface and a front surface opposite the back surface, the metal foam component comprises an open-pored metal foam that is bare and exposed at the front surface of the metal foam component, which is arranged relative to the rotor so that the seal fins or the blade tips directly graze the metal foam, the back surface of the metal foam component is rigidly connected continuously surfacially along the back surface onto the carrier surface of the carrier, whereby the metal foam component is continuously supported along the back surface thereof on the carrier surface of the carrier; and the carrier has holes passing therethrough and opening through the carrier surface to allow gas communication through the holes and from the holes directly into the back surface of the metal foam component and through the open-pored metal foam in a radial gas flow direction that extends radially relative to an axis of the gas turbine engine.