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...

2005-12-22

2008-10-14

Look, Edward (Department: 3745)

Metal working

Method of mechanical manufacture

Impeller making

C415S209400, C415S210100, C029S402010

Reexamination Certificate

active

07434313

ABSTRACT:
A repaired turbine engine stationary vane assembly, including at least one airfoil bonded between inner and outer bands, is provided by a method of providing first and second vane assembly members bonded at respective circumferential edges, for example by brazing or welding. The first vane assembly member includes the outer band, the airfoil, an inner flange, and a first segment of the inner band with a first edge, spaced from the flange and extending between and through inner band circumferential edge portions. The second vane assembly member includes a second segment of the inner band including a second edge of shape and size matched with the first edge and extending through the inner band circumferential edge portions.

REFERENCES:
patent: 4305697 (1981-12-01), Cohen et al.
patent: 5758416 (1998-06-01), Reverman et al.
patent: 6354797 (2002-03-01), Heyward et al.
patent: 7172389 (2007-02-01), Hagle et al.
Co-Pending U.S. Appl. No. 10/989,791, Hagel et al.

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