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AI B) Cl PfUMAHV HOLES SECONDARY DlLIJTION COMBUSTOR THERMOCOUPLE HOI.E and 20,000 pph, temperatures continued to shift, but not as rapidly. It was obvious from these data that increasing quantities of steam were causing significant changes in combustor mixing patterns, the results of which were being detected by increased exhaust temperature spread. Exactly why these combustion changes oc curred was not clear, thus, the long term implication for engine operation was unknown. The overall engine performance was considered acceptable. 1800 Ewa:j:? � 1600 � ::;� f?a: 1400 rn::> lXI ::;0 (.) 1200 1000 -'-- TDC 1 3 BDC 4 5 6 TDC COMBUSTOR NUMBER (CLOCKWISE LOOKING UPSTREAM! Figure 21. Combustor Temperature Profiles with Steam Injection. With: thermocouples at maximum penetration constant mass aver aged turbine inlet temperature. In March 1991, Unit 5 was retested in an attempt to understand the relationship between steam injection and exhaust temperature spread. During the intervening four months, the following changes had occurred: Axial compressor blading was changed. !;, 1 00 DESIGN, INSTALLATION, AND TEST OF A STEAM INJECTION SYSTEM ON AN EARLY FRAME 3 GAS TURBINE IN A COMBINED CYCLE PIPELINE COMPRESSOR STATION 145 LINER CASING THERMOCOUPLE Figure 19. MS 3002 B Combustion Liner. HOLES HOLES DILUTION JET -- 0 NOV. 27/90 ·BEFORE COMBUSTION CHANGES - - - - - - t, NOV. 30/90 ·AFTER COMBUSTION CHANGES wa: w1- 40 1-rn ::><( J:X 20 w �w a: ::>� a: 80 wa.. 80 ::;; � -20 <(::> -40 .:. 0� -60 • �0 -60 -1 00 o• TOC so• 1 20" 1 80" BDC 240° 300° 360" TDC EXHAUST THERMOCOUPLE LOCATIONS !CLOCKWISE LOOKING UPSTREAM) Figure 20. Exhaust Temperature Profiles. With: no steam injection. With the improved combustion uniformity, it was decided to retest steam injection. This time, up to 20,000 pph of steam was injected and again, increases in gas turbine power with steam injection were approximately as expected. However, past 10,000 pph, exhaust spread increased as before, as shown in Figure 17. This time, combustor outlet temperatures were available, as plotted in Figure 21. From 0 to l0,000 pph, temperatures changed somewhat; between 10,000 and 15,000 pph, temperature change reversed direction, and increased dramatically; and between 15,000 • • • A new flow matched gas tip set was tested at the OEM's overhaul facility and installed, and The combustor thermocouples were retracted to their mini mum penetration position of just piercing the liner wall (Figures 16a and 18b). With zero steam injection, exhaust spread was found to be greater now than during the November 27, 1990, tests, as shown in Figure 22, despite the fact that a matched gas tip set had been installed, and all liners and transitions had been carefully inspected for fitup both before, and during installation. Before proceeding with steam injection, exhaust spread was investigated further. Exhaust temperatures from Units 6 and 7 were recorded and compared to those from Unit 5. All three units had similar spreads (l15°F to 135°F), all three units had peaks located about 70 degrees clockwise from top dead center (TDC), while Unit 5 had a second distinct peak at 240 degrees clockwise from top dead center, as shown in Figure 23. All three turbines have identical exhaust systems (leading to waste heat boilers), b u t their inlet systems a r e different. Units 6 and 7 have straight down inlets, while Unit 5 has a side/down inlet (Figure 9). It may be possible that inlet/exhaust configuration causes circumferentially nonuniform flow through the air com pressor (into the liners), so that even with identical combustion All liners were completely dimensionally checked (including louvre gauging).PDF Image | STEAM INJECTION SYSTEM ON AN EARLY FRAME 3 GAS TURBINE IN A COMBINED CYCLE PIPELINE COMPRESSOR STATION
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