Patent ID: 9581035
Date: 2017-02-28
CPC Classifications: F01D,F05D

Claim:
1. A turbine nozzle component, comprising: an inner endwall; an outer endwall radially spaced from the inner endwall; a plurality of nozzle vanes extending between the inner and outer endwalls, the plurality of nozzle vanes having leading and trailing edges; a plurality of turbine nozzle flow paths extending through the turbine nozzle component and generally defined by the inner endwall, the outer endwall, and the plurality of nozzle vanes; and braze preforms positioned in the turbine nozzle flow paths and bonded to at least one of the inner endwall and outer endwall reducing the flow area of the turbine nozzle flow paths, the braze preforms wrapping around the leading and trailing edges of the plurality of nozzle vanes; wherein at least one of the braze preforms comprises a midline break dividing the braze preform into multiple pieces, which are bonded to one of the inner endwall and the outer endwall.