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A process for repairing cracks in a workpiece, such as a turbine engine component, comprises the steps of: providing a workpiece having a crack to be repaired; applying a nickel or cobalt base alloy material to a root of the crack in an amount sufficient to fill a portion of the crack; subjecting th

A process for repairing cracks in a workpiece, such as a turbine engine component, comprises the steps of: providing a workpiece having a crack to be repaired; applying a nickel or cobalt base alloy material to a root of the crack in an amount sufficient to fill a portion of the crack; subjecting the workpiece with the nickel or cobalt base alloy material to a first heat treatment at a temperature in the range of from about 1950 to 2300° F. for a time period in the range of from about 5.0 to 30 minutes; applying a weld material to the crack; and subjecting the workpiece with the weld material to a second heat treatment.

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1. A process for repairing cracks in a workpiece comprising the steps of: providing a workpiece having a crack to be repaired;applying a first layer of a nickel or cobalt base alloy material to a root of said crack in an amount sufficient to fill a portion of the crack;subjecting said workpiece with

1. A process for repairing cracks in a workpiece comprising the steps of: providing a workpiece having a crack to be repaired;applying a first layer of a nickel or cobalt base alloy material to a root of said crack in an amount sufficient to fill a portion of the crack;subjecting said workpiece with said nickel or cobalt base alloy material to a first heat treatment at a temperature in the range of from about 1950 to 2300° F. for a time period in the range of from about 5.0 to 30 minutes;depositing a weld material which assists in providing a diffusion medium having a composition different from said nickel or cobalt base alloy material to said crack using a welding technique subsequent to said first heat treatment;depositing a second layer of a nickel or cobalt based alloy repair material over the weld material; andsubjecting said workpiece with said second layer of a nickel or cobalt based alloy repair material and said weld material to a second heat treatment. 2. The process of claim 1, wherein said step of subjecting said workpiece to a first heat treatment comprises heating said workpiece with said nickel or cobalt base alloy material to a temperature in the range of about 2175 to 2240° F. 3. The process of claim 1, wherein said step of providing a workpiece comprises providing a turbine engine component having a crack to be repaired. 4. The process of claim 1, wherein said step of providing a workpiece comprises providing a turbine engine component formed from a single crystal nickel based superalloy. 5. The process of claim 1, wherein said nickel or cobalt base alloy applying step comprises applying said nickel or cobalt base alloy material in paint form to the crack root. 6. The process of claim 1, wherein said nickel or cobalt base alloy material applying step comprises applying a nickel base alloy repair material comprising a blend of nickel based alloys. 7. The process of claim 1, wherein said nickel base alloy material applying step comprises applying a nickel base alloy repair material comprising a blend of a low melting temperature nickel based alloy brazing alloy and a high melting temperature nickel based alloy. 8. The process of claim 1, wherein said weld material applying step comprises applying a material which is compatible with a material forming said workpiece. 9. The process of claim 1, wherein said weld material depositing step comprises welding said weld material to walls of said crack. 10. The process of claim 9, wherein said welding step comprises welding said material to said walls using a laser. 11. The process of claim 9, wherein said welding step comprises welding said material to said walls using an electro spark deposition technique. 12. The process of claim 9, wherein said welding step comprises welding said material to said walls using a micro-PAW technique. 13. The process of claim 9, wherein said welding step comprises welding said material to said walls using a micro-GTAW technique. 14. The process of claim 9, wherein said welding step comprises welding said material to said walls using EBW. 15. The process of claim 1, wherein said step of subjecting said workpiece to a second heat treatment comprises heating said workpiece to a temperature in the range of from about 1950 to 2300° F. for a time period in the range of about 1 to 20 hours. 16. The process of claim 1, wherein said second layer depositing step comprises applying said second layer of a nickel or cobalt base alloy material in paint form over said weld material. 17. The process of claim 1, wherein said second layer depositing step comprises applying said second layer of a nickel or cobalt base alloy material in paste form over said weld material. 18. A process for repairing a crack in a turbine engine component comprising the steps of: providing a turbine engine component formed from a metallic material and having a crack between about 0.025 inches to about 0.040 inches to be repaired;applying a first layer of a first nickel or cobalt base alloy repair material to a root portion of said crack;subjecting said turbine engine component with said first nickel or cobalt base alloy repair material to a first heat treatment to adhere said nickel or cobalt base alloy repair material to the walls of said crack, to partially fill said crack, and to form a base layer;forming a layer of weld repair material which assists in providing a diffusion medium having a composition different from a composition of said first nickel or cobalt base alloy over said base layer of said first nickel or cobalt base alloy repair material and welding said weld repair material to said walls of said crack;applying a second layer of a second nickel or cobalt base alloy repair material on top of said layer of weld repair material; andsubjecting said workpiece with said second layer of said second nickel or cobalt base alloy repair material and said weld material to a second heat treatment for bonding said second nickel or cobalt base alloy repair material to the walls of said crack. 19. The process according to claim 18, wherein said step of applying a second layer of a second nickel or cobalt base alloy repair material comprises applying a nickel or cobalt base alloy repair material identical to said first nickel base alloy repair material. 20. The process of claim 18, wherein said first nickel or cobalt base alloy repair material applying step comprises applying a nickel base alloy repair material and said forming a layer of weld repair material comprises forming a layer of a nickel based alloy weld repair material. 21. The process of claim 18, wherein said first nickel or cobalt base alloy repair material applying step comprises applying a nickel base alloy repair material and said forming a layer of weld repair material comprises forming a layer of a cobalt based alloy weld repair material. 22. The process of claim 18, wherein said first nickel or cobalt base alloy repair material applying step comprises applying a cobalt base alloy repair material and said forming a layer of weld repair material comprises forming a layer of a nickel based alloy weld repair material. 23. The process of claim 18, wherein said first nickel or cobalt base alloy repair material applying step comprises applying a cobalt base alloy repair material and said forming a layer of weld repair material comprises forming a layer of a cobalt based alloy weld repair material. 24. The process of claim 1, wherein said weld material depositing step comprising depositing said weld material until said weld material is flush with the top of the crack on the component.