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Optimization of aircraft seven stage compressor first stages parameters
- Authors: Popov G.M.1, Matveev V.N.1, Baturin O.V.1, Kolmakova D.A.1
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Affiliations:
- Samara State Aerospace University
- Issue: Vol 11, No 5-1 (2012): Special Issue
- Pages: 191-198
- Section: CONFERENCE MATERIALS
- URL: https://journals.ssau.ru/vestnik/article/view/1864
- DOI: https://doi.org/10.18287/2541-7533-2012-0-5-1(36)-191-198
- ID: 1864
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Abstract
The optimization of multistage compressor of gas turbine engine is considered. Optimization was performed by changing the guide vanes angles of three stages. As a result the increasing of compressor efficiency by 0.3% was achieved on one of the main modes of operation.
About the authors
G. M. Popov
Samara State Aerospace University
Author for correspondence.
Email: grishatty@mail.ru
Engineer
Russian FederationV. N. Matveev
Samara State Aerospace University
Email: tdla@ssau.ru
Doctor of Technical Sciences, Professor
Head of Department of Aircraft Engines Theory
Russian FederationO. V. Baturin
Samara State Aerospace University
Email: oleg.v.baturin@gmail.com
Candidate of Science
Assistant Professor of the Chair of Theory of Engine for Flying Vehicle
Russian FederationD. A. Kolmakova
Samara State Aerospace University
Email: kolmakova.daria@gmail.com
Magistrand
Russian FederationReferences
- Egorov, I. N., Optimization of the gas turbine engine parts using methods of numerical simulation [Текст] / I.N. Egorov, M.L. Kuzmenko, Yu.N. Shmotin, K.S. Fedechkin // ASME paper GT2007-28205.
- Дмитриева, И.Б. Автоматизация создания объёмной модели пера лопатки в ANSYS TurboGrid на базе традиционного представления его геометрии [Текст] / И.Б. Дмитриева, Л.С. Шаблий // Вестник Самарского государственного аэрокосмического университета имени академика С.П. Королёва. – Самара, 2011. – №3 (27). Часть 3. – С. 106-111.
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