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AssigneeMTU Aero Engines AG
InventorsManfred A. Daeubler, Horst Mueller-Wittek, Renate Mendritzki, Ulrike Hain, Werner Humhauser
Estimating the term…
A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a circular ring-shaped outer wall, a circular ring-shaped inner wall, which is located at a short radial distance from the moving blade tips, and includes a joining structure provided in the form of hollow chamber structure between the outer wall and the inner wall. The outer wall is provided in the form of a closed, mechanically stable housing wall of the compressor or turbine stage, and the joining structure provided in the form of hollow chamber structure is joined in a fixed manner to the outer wall and to the inner wall, for example, by soldering, diffusion welding or other joining techniques. The inner wall is provided in the form of a closed, mechanically stable structure, which serves as a run-in lining for the moving blade tips and which is made of a metal woven fabric and/or of a metal felt.
1-10. (canceled)
A ring structure of metal construction for a rotor blade region of axial flow compressor and turbine stages comprising:
The ring structure as recited in claim 1, 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 forming at least one butt joint abutting transitionally on the annular inner wall.
Dependencies are inferred from the claim text.