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Table 4 Optimized design point calculations. erosion, and corrosion are indicated in terms of variation in one or more independent health parameters responsible for gas path components performance. These health parameters influence dependent parameters such as power, thermal effi- ciency, and SFC [27]. In the present work, compressor fouling simulations were carried out by quantifying two independent health parameters: (i) compressor flow capacity change and (ii) compressor isentropic efficiency change. The equations used for fault severity simulations are adopted from Qingcai et al. [23] and are given below:

Table 4 Optimized design point calculations. erosion, and corrosion are indicated in terms of variation in one or more independent health parameters responsible for gas path components performance. These health parameters influence dependent parameters such as power, thermal effi- ciency, and SFC [27]. In the present work, compressor fouling simulations were carried out by quantifying two independent health parameters: (i) compressor flow capacity change and (ii) compressor isentropic efficiency change. The equations used for fault severity simulations are adopted from Qingcai et al. [23] and are given below:

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In the literature, various simulation programs such as G7 pro |4|, GateCycle [25], and IPSEPRO [9] have been imple- mented to simulate gas turbines. In the present work, however, GasTurb 12 is employed owing to its inherent ability to simu- late the effect of fouling and a variable geometry schedule can also be applied to simulate a variable geometry industrial gas turbine. To accomplish the steady state off-design simulation of the Taurus 70 gas turbine, cycle design point calculations are the prerequisites. The design point calculations for the present work has been achieved using some design point input data from the manufacturer catalogue and some assumed values supported by literature as listed in Table 1. oe
In the literature, various simulation programs such as G7 pro |4|, GateCycle [25], and IPSEPRO [9] have been imple- mented to simulate gas turbines. In the present work, however, GasTurb 12 is employed owing to its inherent ability to simu- late the effect of fouling and a variable geometry schedule can also be applied to simulate a variable geometry industrial gas turbine. To accomplish the steady state off-design simulation of the Taurus 70 gas turbine, cycle design point calculations are the prerequisites. The design point calculations for the present work has been achieved using some design point input data from the manufacturer catalogue and some assumed values supported by literature as listed in Table 1. oe
Table 1 Design point input parameters for Taurus 7 industrial gas turbine.
Table 1 Design point input parameters for Taurus 7 industrial gas turbine.
The optimized values of the isentropic and polytropic effi- ciencies and pressure ratios across each major component are given in Table 3 and the complete optimized design point cal- culation values in Table 4. ig. 2 Flowchart of design point and off-design simulations.
The optimized values of the isentropic and polytropic effi- ciencies and pressure ratios across each major component are given in Table 3 and the complete optimized design point cal- culation values in Table 4. ig. 2 Flowchart of design point and off-design simulations.
Table 2 Values of the optimized input variables. Table 3 Optimized values of the design point efficiencies.
Table 2 Values of the optimized input variables. Table 3 Optimized values of the design point efficiencies.
Fig. 4 Effect of fouling on efficiency in compressor map. Fig. 3. Effect of fouling on pressure ratio in compressor map.
Fig. 4 Effect of fouling on efficiency in compressor map. Fig. 3. Effect of fouling on pressure ratio in compressor map.
The quantification of the health parameters is based on cor- relations reported by Escher et al. [28]. It became evident from the present study that for every 1% decrease in isentropic effi- ciency, the mass flow deteriorates by 3%. As pointed out in the literature, the maximum range for mass flow reduction is between 0 and —7.5% and the isentropic efficiency changes between 0 and —2.5% while maintaining the ratio between Am and Ay to 3:1 [23,26]. The effect of fouling on the compres- sor performance map is shown in Figs. 3 and 4. The red line shows the deviation of the pressure ratio curves from the
The quantification of the health parameters is based on cor- relations reported by Escher et al. [28]. It became evident from the present study that for every 1% decrease in isentropic effi- ciency, the mass flow deteriorates by 3%. As pointed out in the literature, the maximum range for mass flow reduction is between 0 and —7.5% and the isentropic efficiency changes between 0 and —2.5% while maintaining the ratio between Am and Ay to 3:1 [23,26]. The effect of fouling on the compres- sor performance map is shown in Figs. 3 and 4. The red line shows the deviation of the pressure ratio curves from the
During the fixed geometry, the VIGV angle setting in Gas- Turb 12 is 0°. It has been observed by various simulations that for each 1° variation in VIGV angle, the mass flow and pres- sure are changed by 1% [32]. For that reason, there is a need to set appropriate numbers for the following factors in the GasTurb 12: Fig. 6 Effect of VIGV change on the PR in compressor map.
During the fixed geometry, the VIGV angle setting in Gas- Turb 12 is 0°. It has been observed by various simulations that for each 1° variation in VIGV angle, the mass flow and pres- sure are changed by 1% [32]. For that reason, there is a need to set appropriate numbers for the following factors in the GasTurb 12: Fig. 6 Effect of VIGV change on the PR in compressor map.
Fig. 7 Effect of VIGV change on the efficiency in compressor map.
Fig. 7 Effect of VIGV change on the efficiency in compressor map.
During part load operation, the power output is reduced by closing VIGVs from 100% load to the required load. In this way the VIGV schedule can change the operating point on the compressor performance map. The compressor perfor- mance maps shown in the Figs. 6 and 7 represent a shift in operating parameters including the compressor mass flow, pressure ratio, and isentropic efficiency. These parameters
During part load operation, the power output is reduced by closing VIGVs from 100% load to the required load. In this way the VIGV schedule can change the operating point on the compressor performance map. The compressor perfor- mance maps shown in the Figs. 6 and 7 represent a shift in operating parameters including the compressor mass flow, pressure ratio, and isentropic efficiency. These parameters
Fig. 8 Effect of parametric study on the thermal efficiency at 100% fouling severity. As shown in Fig. 9, with the increase in ambient tempera- ture the SFC increases gradually, which is not economically desirable. That is the reason why the inlet air cooling process is essential. Similarly, with a gradual increase of relative
Fig. 8 Effect of parametric study on the thermal efficiency at 100% fouling severity. As shown in Fig. 9, with the increase in ambient tempera- ture the SFC increases gradually, which is not economically desirable. That is the reason why the inlet air cooling process is essential. Similarly, with a gradual increase of relative
Fig. 9 Effect of parametric study on SFC at 100% fouling severity.
Fig. 9 Effect of parametric study on SFC at 100% fouling severity.
Fig. 10 Effect of fouling on performance parameters for fixed geometry case. (IAC = Inlet air cooled temperature, NDP = Near Design Point Temperature, HAT = High Ambient Temperature).
Fig. 10 Effect of fouling on performance parameters for fixed geometry case. (IAC = Inlet air cooled temperature, NDP = Near Design Point Temperature, HAT = High Ambient Temperature).
Fig. 11 Effect of fouling on performance parameters with VIGV schedule case. (IAC = Inlet air cooled temperature, NDP = Near Design Point Temperature, HAT = High Ambient Temperature).
Fig. 11 Effect of fouling on performance parameters with VIGV schedule case. (IAC = Inlet air cooled temperature, NDP = Near Design Point Temperature, HAT = High Ambient Temperature).
Fig. 12 Validation of the GasTurb 12 simulation.
Fig. 12 Validation of the GasTurb 12 simulation.
Related topics:
GAS TURBINEOxy-Fuel CombustionCombustion DiagnosticsThermoelectric Generatorsupercritical CO2 cycle
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