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where: such as the compressor, combustor and the turbine are carried out with the aid of developed computer program. In this sec- tion we will discuss the effect of the major parameters (i.e. ambient temperature, pressure ratio, thermal efficiency...). The values of these parameters can be estimated using basic cycle equations given above and assuming variable values for thermodynamic proprieties. All the required readings were taken from the gas turbine model. In the first case, the STIG cycle performance calculated over wide ranges of temperature (0-50°C) and pressure ratio: (1-10) is optimized at standard ambient conditions. In the other hand, these optimal parameters are stabilized by inject- ing suitable amount of steam in the upstream of combustion chamber when the ambient temperature becomes higher ISO conditions. 4.1 Simple Gas Turbine Performances Analysis Without Steam Injection For wide values of inlet temperature, the specific work of the compressor can be plotted against pressure ratio as shown in Figure 5. It can be derived from this figure, that the specific work increases as the pressure ratio increase for a given inlet tem- perature. As for the effect of ambient temperature, the same variation is obtained. This is because, to compress the air at a higher temperature, the compressor needs a more significant work. The efficiency observed decreases as ambient temperature is increased. This can be explained by Figure 6, which indi- cates the influence of ambient temperature on the variation of efficiency as a function of pressure ratio. For high inlet tem- perature (tamb > 30°C), efficiency reaches a maximum at A Bouam et al. / Gas Turbine Performances Improvement Using Steam Injection in the Combustion Chamber 255 ⎧α=h3,g −h2,a ⎪ ⎪β=h3,s−h2,s ⎪γ = ηCC * LCV − h3,g ⎪ ⎨A =(η *LCV)/η (9) 1 The mec ⎪B =w /η ⎪1Cmec ⎪C1=h3,g−h4,g ⎪D1=h3,s−h4,s ⎩ The deviation of power output is summarized here for completeness. Power output is expressed by relating the net output to the difference between the turbine and compressor power: P = m + m * h − h f ) (3,g 4,g) − h − m * h ( a + m * h s The scheme of the proposal analysis out lined above has been numerically studied using simulation computer program already by the authors. The computer program is based on fundamental thermodynamic relations including real gas behavior and the pressure losses [21-23]. 3 TEST DATA The validity of the relations presented above and their applic- ability to estimate the effect of steam injection will be assessed by application to test data from an operating indus- trial gas turbine. The tests are performed on a single shaft gas turbine (GE MS5002) [24]. Table 1 gives manufactures data, at ISO conditions. TABLE 1 Characteristics of the GE MS5002 gas turbine Ut (10) (11) ( ) ( − h a,t ) s,t The overall efficiency of plant is: a,t a cc4 21 P η= Ut s,t P m'*LCV f t = 0.00°C t = 9.00°C t = 15.00°C t = 17.86°C t = 25.00°C t = 32.14°C t = 39.29°C t = 46.43°C t = 50.00°C tcc = 900°C patm =1.0132 bar ηC (%) ηT ηmec Δpcc (%) (%) (%) ηCC ΔpAdm ε (%) (%) 7.376 Cf (-) 45000 40000 35000 30000 25000 20000 15000 10000 5000 0 Caractéristiques of GE MS5002 Caractéristiques of GE MS5002 18000 23 900 45119 1.02 4 2 4p/p6 8 10 21 90 Pmanf (kW) 88 ηTh manf (%) tCC (°C) 4 LCV (GN) (kj/kg) 95 1 RESULTS AND INTERPRETATIONS Figure 5 Specific work of compressor. Calculations of the performance of gas turbine components 95 PC (kW)PDF Image | Gas Turbine Improvement with Steam Injection Combustion Sahara Conditions
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