Sealing system for a turbomachine
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United States of America Patent
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Mar 20, 2018
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N/A
app pub date -
Apr 3, 2013
filing date -
Apr 4, 2012
priority date (Note) -
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Abstract
Disclosed is a sealing system for a turbomachine, in particular for a gas turbine, the sealing system being formed in an annular space between a flow-limiting wall of the turbomachine and at least one rotor blade tip of a rotor blade or an outer shroud arranged on the rotor blade tip, and comprising at least one sealing point. The sealing point comprises at least one run-in coating arranged on the rotor blade tip or on the outer shroud in the direction of the flow-limiting wall of the turbomachine. The invention furthermore encompasses a gas turbine comprising the sealing system.
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