GE94-02: Repair Flow Testing and Calibration Procedures for ...

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GE96‐10N1. Specification for Repair of MS7001 EA, F, FA First Stage Nozzles. July 1998. This specification identifies the requirements for repair of MS7001EA first stage nozzles, which are made from FSX 414 cobalt‐base alloy. The repaired nozzles life should safely achieve regularly scheduled overhaul intervals. GE96‐10N2. Specification for Repair of MS7001 EA, F. FA Second Stage Nozzles. July 1998. This specification identifies the requirements for repair of MS7001EA, F and FA second stage nozzles, which are made from FSX 414 cobalt‐base alloy or GTD222 nickel‐based alloy. The repaired nozzles life should safely achieve regularly scheduled overhaul intervals. GE96‐10N3. Specification for Repair of MS7001 EA, F, FA Third Stage Nozzles. July 1998. This specification identifies the requirements for repair of MS7001EA, F and FA third stage nozzles, which are made from FSX 414 cobalt‐base alloy or GTD 222 nickel‐based alloy. The repaired nozzles life should safely achieve regularly scheduled overhaul intervals. GE96‐11C. Specification for Repair of MS7001 F and FA Combustor Liners. July 1998. This specification identifies the requirements for repair of MS7001 F and FA combustion liners manufactured from Hastelloy X, Haynes 188, Inconel X750 and Nimonic 263 alloys with a thermal barrier coating. GE96‐11T. Specification for Repair of MS7001 F and FA Transition Pieces. July 1998. This specification identifies the requirements for repair of MS7001 F and FA transition pieces manufactured from Hastelloy X and Nimonic 263 with a thermal barrier coating.
GE96‐20M. Eddy Current Measurement of Thickness and Degradation in Advanced Gas Turbine Coating Systems. November 1996. An eddy current method was developed for estimating the relative degradation of the General Electric proprietary GT‐29PLUS coating system on directionally solidified GTD‐111 first stage turbine buckets. The method consisted of recording the magnitude (vector length) of the impedance during a sweep of frequencies from 500 KHz to 6.0 MHz. We then employed the variations of magnitude with frequencies as parameters for the correlation with coating structure and composition. The instrumentation system incorporated an SE Systems, Inc. SmartEDDY 3.0 digital eddy current module, with software modified to conduct a frequency sweep, into a standard Structural Integrity Associates TestPro data acquisition and analysis system. An SE Systems 3 mm. diameter probe in a 5 mm. diameter housing was positioned in a holder that controlled lift‐off and normality. The procedure included balancing (nulling) the instrument at 2.0 MHz at each test location. A Frame 7FA bucket, removed for refurbishment after 18,700 hrs. of operation on natural gas, was sectioned to allow metallographic evaluation of the coating at 50 percent span. The thickness of the interdiffusion layer between plasma sprayed GT‐29 and the substrate alloy and the equivalent thickness of beta cobalt aluminide in the outer layer of the coating were measured at several locations and compared against various eddy current signal parameters involving the magnitude versus frequency response. One parameter ⎯ the rms slope of both the high frequency and low frequency portions of the sweep ⎯ was ultimately selected. Reproducible correlations between coating layer thickness and rms slope were obtained for the particular blade tested. The interdiffusion layer thickness, estimated by the low frequency eddy current parameter, was shown to provide an acceptable indication of relative surface temperature, and the approximate remaining beta aluminide layer thickness could be estimated from the high frequency parameter. The calibration curves for different batches of coated blades were found to be different, requiring reference measurement of each batch at a location of low operating temperature. The procedure developed can be used to compare these batches and insure the selection of representative blade samples for field tests. Sections of a Frame 6B bucket that had operated for about 10,000 hr. were also evaluated by metallography and tested by the eddy current procedure. While only minimal in‐service degradation was found from the metallographic data, the eddy current test results were different and, in turn, appeared to represent differences in the initial coating process.
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