| US 7,546,683 B2 | ||
| Touch-up of layer paint oxides for gas turbine disks and seals | ||
| Brian Thomas Hazel, Cincinnati, Ohio (US); Eva Zielonka Lanman, Milford, Ohio (US); Joseph Aloysius Heaney, Middletown, Ohio (US); and Michael James Weimer, Loveland, Ohio (US) | ||
| Assigned to General Electric Company, Schenectady, N.Y. (US) | ||
| Filed on Dec. 29, 2003, as Appl. No. 10/747,458. | ||
| Prior Publication US 2005/0138805 A1, Jun. 30, 2005 | ||
| Int. Cl. B23P 6/00 (2006.01); B23D 19/10 (2006.01); B23K 9/04 (2006.01) | ||
| U.S. Cl. 29—889.1 [29/402.18] | 21 Claims |
| 1. A method for repairing an imperfection in a corrosion-inhibiting layer paint oxide system comprising a plurality of layers
on a turbine engine component, the method comprising the steps of:
providing a turbine engine component comprising a superalloy substrate, wherein at least a portion of the substrate has been
treated with a corrosion inhibiting paint oxide system comprising aluminia and chromia, wherein an imperfection region is
present on the system exposing the superalloy substrate beneath the system;
providing a touch-up paint comprising alumina particles, an evaporable solvent, and a binder selected from the group consisting
of silicate, silicone, chromate phosphate, siloxane, and combinations thereof;
applying a layer of the touch-up paint to the imperfection region;
drying the layer of touch-up paint; and
curing the layer of touch-up paint at a temperature up to about 1000° F.;
wherein the touch-up paint further comprises additional oxide particles selected from the group consisting of chromia, silica,
titania, zirconia, tantala, and combinations thereof.
|