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AssigneeMTU Aero Engines AG
InventorsRudolf STANKA, Thomas Hess, Karl Maar, Karl-Heinz Dusel
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A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided.
A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring, the casing ring having an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the thermal gas turbine, the damping device comprising:
A method for manufacturing a damping device situatable between a housing wall of a housing of a thermal gas turbine and a casing ring, the casing ring having an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the thermal gas turbine, the method comprising:
Dependencies are inferred from the claim text.