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Effect of non-uniform compressor flow parameters on the characteristics of a gas turbine engine combustion chamber
- Authors: Matveev S.G.1, Orlov M.Y.1, Zubrilin I.A.1, Matveev S.S.1, Tsybizov Y.I.2
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Affiliations:
- Samara State Aerospace University
- «Kuznetsov» plc, Samara
- Issue: Vol 12, No 3-1 (2013): Vestnik SSAU
- Pages: 163-169
- Section: ISSUE WITHOUT SECTION
- URL: https://journals.ssau.ru/vestnik/article/view/75
- DOI: https://doi.org/10.18287/1998-6629-2013-0-3-1(41)-163-169
- ID: 75
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Abstract
A mathematical model of the working process of a gas turbine engine combustion chamber is presented which makes it possible to take into account the residual swirl and radial non-uniformity of the flow velocity at the inlet to the combustion chamber.
About the authors
S. G. Matveev
Samara State Aerospace University
Author for correspondence.
Email: pfu@ssau.ru
Candidate of Technical Science
Associate Professor of the Department of Heat Engineering and Heat Engines
Russian FederationM. Y. Orlov
Samara State Aerospace University
Email: adler65@mail.ru
Candidate of Technical Science
Associate Professor of the Department of Heat Engineering and Heat Engines
Russian FederationI. A. Zubrilin
Samara State Aerospace University
Email: zubrilin416@mail.ru
Laboratory Engineer
Russian FederationS. S. Matveev
Samara State Aerospace University
Email: matveev@ssau.ru
Laboratory Engineer
Russian FederationY. I. Tsybizov
«Kuznetsov» plc, Samara
Email: motor@kuznetsov-motors.ru
Head of the Development Department
Russian FederationReferences
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