Patent ID: 7172389
Filing Date: 2007-02-06
Classification: B23K,B23P,F01D,Y10T

Abstract:
1. A method for making a repaired turbine engine stationary vane assembly comprising a first platform, a second platform radially spaced apart from the first platform, and a plurality of airfoils therebetween, the plurality of airfoils each including a first airfoil end and a second airfoil end spaced-apart from the first airfoil end, comprising the steps of: providing a first vane assembly member including at least a portion of the first platform bonded with the plurality of airfoils at the first airfoil ends, and a second platform first segment having a first edge portion of a first selected peripheral shape bonded with the plurality of airfoils at the second airfoil ends and including material of the second platform between the plurality of airfoils; providing a second vane assembly member comprising a second platform second segment including therein a first recess having a second edge portion substantially of the first selected peripheral shape and of a size sufficient to receive therein the second platform first segment to enable the first and second edge portions to be in juxtaposition; placing the second platform first segment of the first vane assembly member in the first recess of the second platform second segment of the second vane assembly member with the first and second edge portions in juxtaposition; and then, bonding the first vane assembly member and the second vane assembly member about the first and second edge portions to provide a repaired turbine engine vane assembly.