Hybrid turbine tip clearance control system
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United States of America Patent
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Aug 9, 2005
Grant Date -
Jun 16, 2005
app pub date -
Apr 30, 2003
filing date -
Apr 30, 2003
priority date (Note) -
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Abstract
A turbine shroud cooling system used in a gas turbine engine for controlling tip clearance between a turbine shroud assembly and turbine rotor blades comprises a cooling air passage for selectively directing a cooling air flow between components to be cooled and a turbine shroud support assembly for controlling the tip clearance and then later re-directing the cooling air flow to cool a downstream turbine component.
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