Shroud for rotating blades of a turbo machine, and turbo machine
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United States of America Patent
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Nov 5, 2013
Grant Date -
May 5, 2011
app pub date -
Apr 30, 2009
filing date -
May 13, 2008
priority date (Note) -
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Abstract
A shroud for the rotating blades of a turbo machine, particularly a gas turbine, in which shroud is arranged along the circumference of a row of several rotating blades disposed on a rotor and has at least one separation gap along its circumference. The separation gap is formed in zigzag shape and has at least three damping gaps that are distanced from one another and extend at an angle relative to an axis of rotation of the rotor, and adjacent to these, has connection gaps each connecting damping gaps or extending the latter in the direction of shroud edges, wherein, when the rotor rotates, the gap width of damping gaps is reduced until the gap walls forming the damping gaps come to rest against each other.
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