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A method for restoring blade dovetails to their original shape comprising the steps of removing damaged material from a blade dovetail at a damage site, physically depositing a metal at the damage site in an amount sufficient to replace the removed damaged material, and machining the blade dovetail

A method for restoring blade dovetails to their original shape comprising the steps of removing damaged material from a blade dovetail at a damage site, physically depositing a metal at the damage site in an amount sufficient to replace the removed damaged material, and machining the blade dovetail to the original shape.

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1. A method for restoring blade dovetails to their original shape comprising the steps of: removing damaged material only from a contact surface of a blade dovetail at a damage site;said removing step comprising removing said damaged material to a depth sufficient to fully eradicate surface distress

1. A method for restoring blade dovetails to their original shape comprising the steps of: removing damaged material only from a contact surface of a blade dovetail at a damage site;said removing step comprising removing said damaged material to a depth sufficient to fully eradicate surface distress;restoring said contact surface by performing vapor deposition of a metal only at said damage site on said contact surface in an amount sufficient to replace said removed damaged material;said vapor deposition performing step comprising depositing a metal having near parent material chemistry and near parent material properties; andmachining said blade dovetail to said original shape,wherein said performing vapor deposition of said metal is performed at a rate between 10 and 50 micrometers per minute,wherein said removing said damaged material comprises the step of machining said dovetail to an approximate depth between five and fifteen mils; andperforming the additional step of shot peening said blade dovetail. 2. The method of claim 1 comprising the additional step of applying an anti-galling material to a surface of said machined dovetail. 3. The method of claim 2 wherein said applying said anti-galling material comprises applying an anti-galling material selected from the group consisting of aluminum-bronze, copper-nickel, and copper-nickel-indium. 4. The method of claim 1 wherein said removing damaged material from said blade dovetail comprises removing material from a blade dovetail selected from the group consisting of compressor blade dovetails and fan blade dovetails. 5. The method of claim 1 wherein said performing vapor deposition comprises performing physical vapor deposition in a manner selected from the group consisting of cathodic arc vapor deposition, electron beam physical vapor deposition, and electron beam flash vapor deposition. 6. A method for restoring blade dovetails to their original shape comprising the steps of: removing damaged material only from a contact surface of a blade dovetail at a damage site;said removing step comprising removing said damaged material to a depth sufficient to fully eradicate surface distress;restoring said contact surface by performing vapor deposition of a metal only at said damage site on said contact surface in an amount sufficient to replace said removed damaged material;said vapor deposition performing step comprising depositing a metal having near parent material chemistry and near parent material properties;machining said blade dovetail to said original shape,wherein said performing vapor deposition of said metal comprises physically depositing a metal consisting of Ti-8Al-1V-1Mo; andwherein said performing vapor deposition of said metal is performed at a rate between 10 and 50 micrometers per minute. 7. A method for restoring blade dovetails to their original shape comprising the steps of: removing damaged material only from a contact surface of a blade dovetail at a damage site;said removing step comprising removing said damaged material to a depth sufficient to fully eradicate surface distress;restoring said contact surface by performing vapor deposition of a metal only at said damage site on said contact surface in an amount sufficient to replace said removed damaged material;said vapor deposition performing step comprising depositing a metal having near parent material chemistry and near parent material properties; andmachining said blade dovetail to said original shape,wherein said performing vapor deposition comprises performing physical vapor deposition in a manner selected from the group consisting of cathodic arc vapor deposition, electron beam physical vapor deposition, and electron beam flash vapor deposition; andwherein said performing said performing vapor deposition is performed at a pressure between 10−3 and 10−6 torr; andwherein said performing vapor deposition of said metal is performed at a rate between 10 and 50 micrometers per minute. 8. The method of claim 7 wherein said performing said performing vapor deposition is performed at a pressure of approximately 10−4 torr. 9. The method of claim 7 wherein said performing vapor deposition of said metal is performed at a rate of approximately 20 micrometers per minute. 10. The method of claim 7, wherein said performing vapor deposition of said metal comprises physically depositing a metal selected from the group consisting of Ti-6Al-4V and Ti-8Al-1V-1Mo. 11. The method of claim 7, wherein said performing vapor deposition of said metal comprises physically depositing one of Ti-6Al-4V and a titanium alloy different than Ti-6Al-4V.