Abstract
This paper shows the effect of excess air on combustion gas temperature at turbine inlet, and how it determines power and thermal efficiency of a gas turbine at different pressure ratios and excess air. In such a way an analytic Equation that allows calculating the turbine inlet temperature as a function of excess air, pressure ratio and relative humidity is given. Humidity Impact on excess air calculation is also analyzed and presented. Likewise it is demonstrated that dry air calculations determine a higher level for calculations that can be performed on wet air.
Highlights
Evolution of gas turbines has evolved together with aero thermodynamics and metallurgy, such relationship has made possible for today’s gas turbines to withstand temperatures in the 1700 ̊C range [1,2], pressure ratios up to 34:1 [1,2], internal compressor and turbine efficiency up to 90% [3] and overall thermal efficiency up to 40% [3]
This paper shows the effect of excess air on combustion gas temperature at turbine inlet, and how it determines power and thermal efficiency of a gas turbine at different pressure ratios and excess air
Likewise it is demonstrated that dry air calculations determine a higher level for calculations that can be performed on wet air
Summary
Evolution of gas turbines has evolved together with aero thermodynamics and metallurgy, such relationship has made possible for today’s gas turbines to withstand temperatures in the 1700 ̊C range [1,2], pressure ratios up to 34:1 [1,2], internal compressor and turbine efficiency up to 90% [3] and overall thermal efficiency up to 40% [3]. The most spectacular improvement that the gas turbine has even experimented is, perhaps, the increase of the gas turbine inlet temperature. This has been possible thanks to improvements on the turbine blade cooling techniques, and metallurgical advances. It is known that the temperature during steady combustion in the combustion zone, greatly exceeds the maximum allowable temperature by the turbine blades on the first stage, an increase in excess air is needed to bring down the combustion gas temperature to allowable values at the turbine inlet. The objective of this work is to calculate the required excess air in the combustion chamber to reach an exhaust gas temperature allowable by the turbine first stages blades. The effect of relative humidity on the gas turbine is wide discussed at the paper of I
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