Method for repairing a turbine engine vane assembly and...

Details Method for repairing a turbine engine vane assembly and... Method for repairing a turbine engine vane assembly and...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) B23P 6/00 (2006.01) F01D 5/12 (2006.01)

Patent

CA 2571900

A repaired turbine engine stationary vane assembly (10), including at least one airfoil (16) bonded between inner (14) and outer (12) bands, is provided by a method of providing first (28) and second (30) vane assembly members bonded at respective circumferential edges (36,42), for example by brazing or welding. The first vane assembly member (28) includes the outer band (12), the airfoil (16), and inner flange (18), and a first segment (34) of the inner band (14) with a first edge (36), spaced from the flange (18) and extending between and through inner band circumferential edge portions (32,33). The second vane assembly member (30) includes a second segment (40) of the inner band (14) including a second edge (42) of shape and size matched with the first edge (36) and extending through the inner band circumferential edge portions (32,33).

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