Email this article 
Improving the high pressure compressor efficiency by optimizing the stator blades angles
- Authors: Popov G.M.1
-
Affiliations:
- Samara State Aerospace University
- Issue: Vol 11, No 3-2 (2012): Special Issue
- Pages: 235-241
- Section: CONFERENCE MATERIALS
- URL: https://journals.ssau.ru/vestnik/article/view/2179
- DOI: https://doi.org/10.18287/2541-7533-2012-0-3-2(34)-235-241
- ID: 2179
Cite item
Full Text
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 of the Theory of Engine for Flying Vehicle Department
Russian FederationReferences
- Optimization of the gas turbine engine parts using methods of numerical simulation [Текст] / I.N. Egorov, M.L. Kuzmenko, Yu.N. Shmotin [et al.] // 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 // Вестн. СГАУ. – Самара, 2011. – №3 (27). - Ч. 3. – С. 106-111.
Supplementary files
