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Shroud for a gas turbine engine

  • US 10,450,897 B2
  • Filed: 07/18/2016
  • Issued: 10/22/2019
  • Est. Priority Date: 07/18/2016
  • Status: Expired due to Fees
First Claim
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1. A shroud segment for a gas turbine engine, the gas turbine engine including a rotor blade stage and a nozzle stage, the shroud segment comprising:

  • a forward end, the forward end defining an outer wall of the rotor blade stage; and

    an aft end, the aft end defining an outer wall of the nozzle stage, the aft end defining at least a portion of an opening therethrough for receipt of a nozzle,wherein the forward end and the aft end form a single, continuous component, andwherein the aft end is angled radially outward with respect to the forward end.

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