Patent ID: 9533485
Date: 2017-01-03
CPC Classifications: B22F,B23K,B33Y,F01D,F04D,F05D,Y02P,Y10T

Claim:
1. A method of manufacturing a variable vane assembly for a compressor of a gas turbine engine, the variable vane assembly including an inner shroud and an outer shroud radially spaced apart from each other to define therebetween an annular gas path through which a plurality of variable vanes radially extend between the inner and outer shrouds, each of the variable vanes is pivotable through a vane pivot arc about a respective span-wise vane axis and has a vane airfoil with an overhang portion disposed at a trailing edge thereof, the method comprising: forming a plurality of projections on at least one of the inner and outer shrouds, the projections protruding from an annular boundary surface into the annular gas path, each of the projections being at least partially circumferentially disposed between two of said variable vanes and located adjacent the overhang portion of each of said vane airfoils, including: