By A M Y Razak
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Extra info for Industrial gas turbines: Performance and operability
Example text
However, the increase in the number of stages will also increase the pressure ratio of the compressor. Thus the decrease in compressor isentropic efficiency with pressure ratio is observed as shown in Fig. 11. 12 Polytropic process of a multi-stage compressor. © 2007 by Taylor & Francis Group, LLC Thermodynamics of gas turbine cycles 31 Similarly, it can be shown that, for a turbine, the isentropic efficiency will increase with pressure ratio and this is due to the reheating of the gas entering the next turbine stage due to the losses in the previous stage.
There are many definitions of these laws, particularly the second law of thermodynamics. The following definitions will be used. 1 The first law of thermodynamics The first law of thermodynamics states simply that energy cannot be created or destroyed but can only be converted from one type or form to another. For example, if we supply 10 MJ of heat into a thermodynamic system operating in a cycle to produce work, then only up to 10 MJ of work can be produced. 2 The second law of thermodynamics The second law of thermodynamics is normally associated with a heat engine.
55, the discharge temperature, T2, is calculated. e. H2 – H1). 3. 13 Combustion charts Combustion temperature rise (K) The process described above may also be used to compute the heat input in a practical gas turbine cycle, taking into account the variation of specific heats or enthalpies during combustion. In practice, however, the heat input is computed from the combustion chart for a given fuel. The following describes the computation of the combustion temperature rise using combustion charts.
