×

Segmented ceramic matrix composite turbine airfoil component

  • US 8,511,980 B2
  • Filed: 07/23/2012
  • Issued: 08/20/2013
  • Est. Priority Date: 01/28/2009
  • Status: Active Grant
First Claim
Patent Images

1. A segmented component for a gas turbine engine, the component comprising:

  • a gas path portion for interacting with gas flow in the gas turbine engine, the gas path portion comprising;

    a forward portion forming a leading edge of a stationary vane;

    an aft portion forming a trailing edge of the stationary vane; and

    a plurality of middle portions forming a pressure side and a suction side of the stationary vane;

    wherein the component is divided into axially aligned segments comprising;

    a forward segment;

    an aft segment; and

    a plurality of middle segments axially stacked between the forward segment and the aft segment, the plurality of middle segments comprising radially elongate ceramic matrix composite material plates, each plate comprising;

    planar forward and rear surfaces that are positioned between the forward segment and the aft segment; and

    sides forming segments of the pressure side and suction side of the gas path portion.

View all claims
  • 4 Assignments
Timeline View
Assignment View
    ×
    ×