A program was conducted to establish cost effective repair procedures for conventionally cast turbine airfoils. Components selected for repair were the TF39 first and second stage turbine vanes and the TF39 first stage turbine blade as determined by a Phase I survey of ALC centers. Processes investigated include Activated Diffusion Healing (ADH) of turbine vanes and Activated Diffusion Bonding (ADB) of turbine blades by the mini-bond process. Pilot line processing of Stage I HPT blades provided an unsatisfactory yield due to a need for process control improvements. Action was taken to revise the Stage I HPT blade program to include use of MTL's new and improved mini-bonder and to try furnace ADB for additional attempts at bonding squealer tips and end caps to blade airfoils to obtain higher yields. TF39 Stage I HPT vanes and TF39 Stage II HPT vanes were successfully processed through ADH repair by the Manufacturing Technology Laboratory and shipped to the General Electric Aviation Service Shop in Cincinnati for final processing and inspection. Representative components of each stage were subjected to 1000 'C' cycles in a TF39 engine test vehicle, inspected, and then evaluated to determine the degree of success for each repair.
Description:
Final technical rept. 15 May 76-1 Feb 79
Pages:
39
Report Date:
APR 1979
Contract Number:
F3361576C5094
Report Number:
B816140
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