Version 1
: Received: 19 September 2023 / Approved: 20 September 2023 / Online: 21 September 2023 (08:53:30 CEST)
How to cite:
Andrew, S.; Dehghaniyan, S. Numerical Investigation of Geometry Effect Channel on Fuel Source Flow Distribution in Micro Gas Turbine Annular Combustor. Preprints2023, 2023091440. https://doi.org/10.20944/preprints202309.1440.v1
Andrew, S.; Dehghaniyan, S. Numerical Investigation of Geometry Effect Channel on Fuel Source Flow Distribution in Micro Gas Turbine Annular Combustor. Preprints 2023, 2023091440. https://doi.org/10.20944/preprints202309.1440.v1
Andrew, S.; Dehghaniyan, S. Numerical Investigation of Geometry Effect Channel on Fuel Source Flow Distribution in Micro Gas Turbine Annular Combustor. Preprints2023, 2023091440. https://doi.org/10.20944/preprints202309.1440.v1
APA Style
Andrew, S., & Dehghaniyan, S. (2023). Numerical Investigation of Geometry Effect Channel on Fuel Source Flow Distribution in Micro Gas Turbine Annular Combustor. Preprints. https://doi.org/10.20944/preprints202309.1440.v1
Chicago/Turabian Style
Andrew, S. and Sanaz Dehghaniyan. 2023 "Numerical Investigation of Geometry Effect Channel on Fuel Source Flow Distribution in Micro Gas Turbine Annular Combustor" Preprints. https://doi.org/10.20944/preprints202309.1440.v1
Abstract
The present distribution examines the effects of nozzle diameter, inlet mass rate, and channel geometry on the fuel distribution in annular combustion chambers of micro gas turbines, taking into account the importance of more uniform fuel distribution in the nozzles connected to the fuel supply channels. A comparison has been made between the numerically calculated pressure drop between the inlet and outlet of the fuel supply nozzle and the experimental value obtained. All fuel supply nozzles with a diameter of 500 micrometers are considered for the micro gas turbine. A more uniform distribution results in better combustion and higher efficiency. A geometrical change in the design of the fuel supply nozzle improved the uniformity of the flow distribution without increasing the pressure drop.
Keywords
Micro gas turbine, fuel supply nozzle, combustion chamber, fuel distribution.
Subject
Engineering, Aerospace Engineering
Copyright:
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
