Abstract
The validity of the gas turbine unit model largely depends on the accuracy of the flue gas temperature value calculation at the gas turbine inlet (TIT). This temperature is determined by the maximum combustion temperature. In variable running mode, the temperature value is regulated by changing the ratio of air and fuel at the inlet to the combustion chamber. The paper presents a model of a gas turbine combustion chamber using Modelica, an object-oriented language for modeling complex physical systems with the aim of determining the temperature of combustion flue gases, specific heat capacity, enthalpy, and flue gas composition at different gas turbine loads.
Highlights
The combustion chamber is an important link in the modeling of a gas turbine unit
The validity of the gas turbine unit model largely depends on the accuracy of the flue gas temperature value calculation at the gas turbine inlet (TIT)
As the range of interpolated values covers the temperature ranges of 300-1000 and 10005000 K these interpolations show large deviations in the calculation of the flue gas temperature in the combustion chamber of the gas turbine, which can be up to 100 K. The reason for this phenomenon lies in the fact that the temperature range of combustion chambers are in the interval of 900-1250 K which just falls between these two intervals
Summary
The combustion chamber is an important link in the modeling of a gas turbine unit. The exhaust gas values from the gas turbine and their magnitude outlet from the combustion chamber affects the accuracy of the calculation of the entire gas turbine model. All of the combustion (or heat exchange) processes in gas or steam turbines can be improved and optimized by using various machine learning methods [7,8,9,10] The advantage of these approaches is in very low relative error in comparison with the available data. As the range of interpolated values covers the temperature ranges of 300-1000 and 10005000 K these interpolations show large deviations in the calculation of the flue gas temperature in the combustion chamber of the gas turbine, which can be up to 100 K The reason for this phenomenon lies in the fact that the temperature range of combustion chambers are in the interval of 900-1250 K which just falls between these two intervals.
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