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Metallic ceramic spool for a gas turbine engine

  • US 8,984,895 B2
  • Filed: 07/11/2011
  • Issued: 03/24/2015
  • Est. Priority Date: 07/09/2010
  • Status: Active Grant
First Claim
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1. A gas turbine engine, comprising:

  • at least one turbo-compressor spool assembly, wherein the at least one turbo-compressor spool assembly comprises a compressor in mechanical communication with a turbine, a volute directing an inlet gas towards an inlet of a rotor of the turbine and a shroud adjacent to the rotor of the turbine, the shroud directing an outlet gas towards an outlet of the at least one turbo-compressor spool assembly; and

    a clearance control device to substantially maintain, during the at least one turbo-compressor spool assembly operation, an operational clearance between the rotor and shroud at a level no greater than about 110% of a non-operational clearance between the rotor and shroud when the at least one turbo-compressor spool assembly is non-operational; and

    wherein the clearance control device comprises;

    (a) a metallic shroud carrier connected to an engine housing and case and to the shroud, the shroud being ceramic, (b) a labyrinth metallic seal sleeve, and (c) the volute comprising a labyrinth seal engaging the labyrinth metallic seal sleeve, the labyrinth seal and seal sleeve sealing substantially against gas flow.

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