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DESIGN, INSTALLATION, AND TEST OF A STEAM INJECTION SYSTEM ON AN EARLY FRAME 3 GAS TURBINE IN A COMBINED CYCLE PIPELINE COMPRESSOR STATION 85 84 83 82 � > 81 u 139 creased by 40 gpm to meet the steam injection requirements. A duplicate of an existing demineralzer plant increased the rated capacity from 75 gpm to 150 gpm. Careful inspection of gas turbine internals was conducted at site during unit overhaul. This review confirmed that the turbine was in good mechanical condition. A decision was made to apply a thermal barrier coating on the combustor liners and the transition pieces to increase service life. In addition, a special wheel inspec tion program was conducted to evaluate the life of existing "com posite design" wheels on this unit. The wheels had no indication of any defects in the bore or under the dovetail roots. The welded joints were inexcellent condition, based on the NDT and transverse hardness tests. To minimize risks associated with retrofit designs, a decision was made to work with vendors who had either the know how or demonstrated experience with such steam injection systems. The system feasibility study along with various design features are outlined. The steam injection system was fabricated, installed, and tested within budget and on schedule. The results of these efforts are also described. GAS TURBINE PERFORMANCE MODEL In March 1989, limited performance tests were conducted on Unit 5 (Model B) to establish a performance model for the gas turbine. Some data were gathered on Units 6 and 7 (Model F) to validate this model. The model is based on the schematic outlined in Figure 1. wz uu:: wu. 80 79 78 76 1.0 1.5 2.0 2.5 -{TN + 125 1!1 140 ® 155.86 A. 170 'I' 185 +200 3.0 3.5 Figure 2. MS 3002 Compressor Turbine Efficiency. PRESSURE RATIO with vane position, it was necessary to produce aerodynamic characteristics at minus five degrees, minus one degree, plus three degrees, plus seven degrees, plus 12 degrees, and plus 22 degrees. The vane midsection suction side and trailing edge is shown in Figure 3 at these positions. A brief illustration of the variation in properties with vane angle is shown in Figure 4 for peak efficiency at each vane position. All detailed characteristics were incorporated into the perfor mance model and compressor design point values adjusted until a Figure 1. MS 3002 Performance Program Schematic. Flows, temperatures, and pressures at each of locations 0 to 12 are determined from component characteristics, and fuel (and steam) input. A steady state solution is achieved when cycle parameters upstream and downstream of each component are consistent with the component's aerodynamic performance. Some points of interest in the performance model development are: • Compressor turbine vane and blade geometry was input to a meanline aerodynamic analysis program and stage characteristics (swallowing capacity, efficiency and exist flow angle) were calcu lated. The efficiency at which power is extracted from the gases is shown in Figure 2, flowing from compressor turbine inlet pressure to exit pressure as a function of stage inlet temperature and shaft speed. • Power turbine vane and blade geometry was determined from the available site manuals, drawings, and throat gauging informa tion. Because the power turbine vane can vary from minus five degrees (fully closed) to plus 22 degrees (fully open) during turbine operation, and stage characteristics do not vary linearly +22' +12' ·5" Figure 3. Power Turbine Vane at Various Positions. 77PDF Image | STEAM INJECTION SYSTEM ON AN EARLY FRAME 3 GAS TURBINE IN A COMBINED CYCLE PIPELINE COMPRESSOR STATION
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