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146 PROCEEDINGS OF THE TWENTY-FIRST TURBOMACHINERY SYMPOSIUM ® NOV 27/90 BEFORE COMBUSTION CHANGES A- - - - NOV 30/90 AFTER COMBUSTION CHANGES 1!1 --- --- MAR 12/91 NEW GAS FUEL TIPS ----------------- -- 0 UNIT NO.5 - - - - /:;. UNIT NO. 6 o• TDC 60' 120' 180' 240' BDC EXHAUST THERMOCOUPLE LOCATIONS ICLOCKWtSE LOOKING UI'STREAMI 300' 360' TDC �/1� / ID ID.. I ---- ®J �-_-------- -100 -t----------- 410 TDC -:.g_ : BDC COMBUSTOR NUMBER 8 TDC Figure 22. Exhaust Temperature Profile. With: no steam injection. hardware, different air/fuel ratios would exist in adjacent combus tors, and low exhaust spread would never be achieved. A touch pad temperature probe was available, so to investigate the previously mentioned possibility, the exposed liner casing surface temperature was measured one inch upstream of the insulation sheath and circumferentially centered between the ig niter mounting flange and the cross flame tube pipe (Figure 11) for all three units and plotted in Figure 24. Because of natural convec tion of the room air around the engine, the top two (1 and 6) liner casings would be expected to run a little hotter than would the bottom two (3 and 4) liner casings. Units 6 and 7 tend to follow this trend while casing 6 on Unit 5 is about 20°F lower than would be expected, possibly confirming the idea that compressor exit flow is not uniformly distributed into Unit 5's liner casings. Figure 24. Linear Casing Upstream Temperature Difef rences. . Mid�ay between the downstream edge of the liner casing msulatton sheath and the bellows clamp (Figure 16b), the exposed liner casing surface temperature was measured over the outboard 180 degrees (from TDC to BDC). If combustion uniformity exists, temperatures at corresponding positions on liner pairs 1 and 6, 2 and 5, and 3 and 4, should be similar. The maximum differences between pairs at similar surface locations are shown in Figure 25. Unit 7 has consistently similar liner casing temperatures, while Unit 5 has variations of up to 95°F, implying significant differenc es in combustion patterns between liners. The conclusion reached at this stage was that variation in liner-to-liner combustion patterns _ --- 0 UNITN0.7 100 ;:;:; 440 a:::> � ::!I! ! 4 3 0 - A.,,_'' / /:;. ---- - - - - - - /:;. �"-,/ a:� 4 2 0 ' o. - - - - - - :: - -o-- ___ -a' -- 0 UNIT NO.5 ----- /:;. UNIT NO.6 ------ 0 UNITNO.7 ------- � 40 20 0 ::!I!! !;; ::>< /,-6,.--A.,'' / 20 i!i // ® UNIT N0.5 MAR 12/91,5:45P M A---- UNIT N0.6MAR 12/91,5:00PM ® - · - -- - UNIT N0.7MAR 12/91,5:30PM 100 80 100 � 80 w0: 80 wiii �-20 •ID J ' --[j � � -80 -100 � -60 0 'A> ·40 ..:.\I o• 60' 120" 180" BDC 240" aoo• 360" TDC O+- 0 20 40 60 80 100 1� 1� 180 180 TDC EXHAUST THERMOCOUPLE LOCATIONS !CLOCKWISE LOOKING UPSTREAM) TDC BDC Figure 23. Exhaust Temperature Profiles. With: base firing, no steaminjection. 11,2,3• CW:4,5,8·CCW) Figure25.LinearCasingDownstreamTemperatureDifef rences. ------- -- ----- DEGREES FROM TDCPDF Image | STEAM INJECTION SYSTEM ON AN EARLY FRAME 3 GAS TURBINE IN A COMBINED CYCLE PIPELINE COMPRESSOR STATION
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