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Gas Turbine Repair Technology GE

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Gas Turbine Repair Technology sites for existing information and programs. Figure 19 shows a Frame 7B rotor that has been converted to a Frame 7E configuration using several new wheels and buckets. Figure 19. Upgraded turbine rotor Combustion Hardware In general, there are two primary failure modes associated with all combustion hardware. One is wear at the mating surfaces that connect the combustion components to each other and to the remainder of the turbine. The other is degradation of the Thermal Barrier Coating (TBC) system. TBCs and their application will be thoroughly addressed in another section of this paper. However, in order to more closely monitor the degradation of the TBC system, global I&RS service centers have recently introduced non- destructive thickness surveys for combustion components as a part of their incoming inspec- tions. This process allows the I&RS service cen- ter process engineers to better assess the ability of an existing coating to remain serviceable for another inspection interval without replace- ment. This process is shown in Figure 20. A recent addition to GE’s service offerings is re- furbishment of 6FA combustion components. Tooling fixtures and methods for the repair of all 6FA combustion components have been de- veloped. 6FA combustion liners are very similar to the 7 and 9FA DLN-2 designs. However, the transition pieces are quite different because the unit only has six combustion cans. Combustor A critical repair operation for louvered com- bustion liners is air-flow testing. Flow testing as- sures that each combustion liner in the set is flowing the same amount of air, thus minimiz- ing temperature variances. (See Figure 21.) When a liner is tested, it is placed on the flow check machine and a vacuum is drawn through the liner. The test machine calculates the effec- tive air flow area. A determination is then made as to whether corrections are necessary. Repair procedures for all types of Dry Low NOx (DLN) components have been developed. On DLN-1, procedures have been established for the restoration of the liner body, venturi, and the cap. They may include repair or replace- ment of fuel nozzle collars and other minor piece parts. DLN-2 liners require a repair operation that re- moves all body distortion by straightening and rounding the liner wall, returning the compo- GE Power Systems ■ GER-3957B ■ (04/01) 12 Figure 20. Non-destructive thickness survey for TBC on transition pieces

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