This paper describes models for a transient analysis of heavy duty gas turbines, and presents dynamic simulation results of a modern electricity generation engine. Basic governing equations are derived from integral forms of unsteady conservation equations. Mathematical models of each component are described with the aid of unsteady one-dimensional governing equations and steady state component characteristics. Special efforts have been made to predict the compressor characteristics including the effect of movable vanes, which govern the running behavior of the whole engine. The derived equation sets are solved numerically by a fully implicit method. A controller model that maintains constant rotational speed and target temperature (turbine inlet or exhaust temperature) is used to simulate real engine operations. Component models, especially those of the compressor, are validated through a comparison with test data. Simulated is the dynamic behavior of a 150MW class engine. The simulated time-dependent variations of engine parameters such as power, rotational speed, fuel, temperatures and guide vane angles are compared with field data. Simulated results are fairly close to the operation data.
This work presents an aerothermodynamic modeling of a cooled turbine blade and the performance analysis of a turbine stage having cooled nozzle blades with trailing edge coolant ejection. A mean line analysis, based on the well-known Ainley-Mathieson scheme, is adopted for the basic loss prediction of the blade rows without cooling. A unique model regarding the interaction between coolant and main gas is proposed. The interactions considered are the heat transfer from main gas to coolant and the temperature and pressure losses by the mixing of two streams due to the trailing edge coolant ejection. For a model turbine stage with nozzle cooling, parametric analyses are carried out to investigate the effect of main design variables (amount of coolant flow, coolant temperature and coolant ejection area) on the stage performance. The influences of coolant mass flow ratio and temperature on the mixing loss and specific work are investigated. The results are also rearranged to investigate the effect of blade temperature on the specific work. Analysis is also carried out by varying the ejection area, which may give useful criteria in determining the coolant condition and ejection hole size of real gas turbine engines.
Q ) mutant phage k is de®cient in the synthesis of the proteins involved in cell lysis and k DNA packaging. As a result, the replicated Q ) k DNA containing a cloned gene is not easily coated by a phage head and remains naked for the ample expression of the cloned gene, and also the host cells do not lyse easily and larger amounts of cloned gene products are produced. In a two-phase operation, the ®rst phase is operated at a low temperature to keep the phage in the lysogenic state for cell growth and cloned gene stability, while the second phase is operated at a high temperature to induce the lytic state for the am-pli®cation of the cloned gene and overproduction of its product. This two-phase operation was optimized by determining both the optimal temperatures for the growth and production phases and the optimal switching time between the growth to the production phase. The optimal temperatures for growth and production phases were 33 and 40°C, respectively. The optimal switching time was 3 h. The recombinant b-galactosidase production using this optimal process was about 20 times higher than in the single-copy lysogenic state.
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