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Turbine shroud gas path duct interface

  • US 8,157,511 B2
  • Filed: 09/30/2008
  • Issued: 04/17/2012
  • Est. Priority Date: 09/30/2008
  • Status: Active Grant
First Claim
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1. A sealing arrangement for a gas path of a turbine engine, the arrangement comprising:

  • a static shroud assembly mounted to an engine case and having an axially-extending annular platform surrounding a rotatable airfoil array, the platform having an inner side and an outer side and extending from a leading edge to a trailing edge, the shroud platform having a circumferentially extending chamfer along the outer side at the platform trailing edge;

    an annular duct extending downstream from the shroud platform trailing edge the shroud platform and the duct defining a portion of the engine main gas path, an axially extending annular gap provided between the shroud platform trailing edge and a leading end of the duct, the duct leading end having an inner side and an outer side, the duct having a circumferentially extending chamfer along the outer side at the leading end; and

    a compliant annular seal extending between and engaging co-operating annular sealing faces provided by the shroud chamfer and the duct chamfer, thereby sealing the annular gap.

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