Patent ID: 8061965

Claim:
A ring structure of metal construction for a rotor blade region of axial flow compressor and turbine stages comprising: an annular outer wall; an annular inner wall spaced adjacent with a radial clearance from blade tips of the rotor blade region; a connecting structure positioned between the outer wall and the inner wall and designed as a hollow-chamber structure, the outer wall being designed as a closed, mechanically stable housing wall of the compressor or turbine stage, the connecting structure connected to the outer wall and the inner wall, and the inner wall forming a run-in lining coating for the blade tips, the inner wall being designed as a whole as a closed, continuous and mechanically stable structure of at least one of a metal woven fabric and a metal felt; and wherein the at least one of the metal woven fabric and the metal felt form the intrinsically closed, annular inner wall, the at least one of the metal woven fabric and the metal felt being joined to one another to form at least one butt joint abutting transitionally on the annular inner wall.