I have studied a book called Thermal Design and Optimization (adrian bejan et al.).
Sections 2 and 3 of this book explain how the mass flow rate of fuel and air in a gas turbine can be calculated based on the products of combustion.
Now I have a question, when I calculate this method for a real case study, I don't get the right value for fuel flow and air mass flow.
In fact, when I validat my calculations with the example in this book, all the calculations are correct, but this is not the case in the actual case study, and the air mass flow rate is half the actual value.
However, I do not know where I am wrong.
Please help me if you can.
how can I calculate the mass flow rate of fuel and air in a gas turbine acording to combustion products?
Dear Reza Ramezanpour Jirandeh
Please have a look on this
https://www.grc.nasa.gov/www/k-12/airplane/fuelfl.html
regards
Ahmed
Dear Ahmad
Thank you.
Definitely, your help has been useful.
But in these calculations there is a factor called adiabatic efficiency (nb) that I do not know what it is and how I can calculate it. If you can help me.
In addition, in my question, fuel and air mass flow rate are obtained according to the composition of the combustion products.
Regards
Hi,
you could use https://github.com/oemof/tespy/ for validation purposes. The online documentation (https://tespy.readthedocs.io/) provides a lot of examples as well, stoichiometry equations are supplied here: https://tespy.readthedocs.io/en/main/api/tespy.components.html#tespy.components.combustion.combustion_chamber.CombustionChamber.stoichiometry (implicit formulation, therefore might be hard to read).
An example of a combustion chamber can be downloaded here, https://github.com/oemof/oemof-examples/blob/master/oemof_examples/tespy/combustion/combustion_chamber.py. Instead of specifying thermal input and lamda, you could also supply flue gas mass flow with CO2 share in flue gas to obtain a solution.
Best
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