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Numerical investigation multifuel combustion gas turbine combustion chamber module
- Authors: Malygina M.V.1
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Affiliations:
- Rybinsk State Academy of Aviation Technology named after P.A. Solovyev
- Issue: Vol 10, No 3-1 (2011): Special Issue
- Pages: 143-150
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/1741
- DOI: https://doi.org/10.18287/2541-7533-2011-0-3-1(27)-143-150
- ID: 1741
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Abstract
There are presented the results of multifunctional combustion modules operation process investigation that forms primary combustion zone in gas turbines combustion chambers. There are found air mass flows ratios through contours of the swirling flows that provide air-fluel ratio distribution required in volume of premixing zone. It is defined angle air swirling flow that allows to reach a compromise4 between a values of hudravlic losses and a volume of paraxial zone ot reverse flows that determine flame stabilization conditions in case of “lean” combustion (α>1,5).
About the authors
M. V. Malygina
Rybinsk State Academy of Aviation Technology named after P.A. Solovyev
Author for correspondence.
Email: slager89@mail.ru
Student
Russian FederationReferences
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