Improving the high pressure compressor efficiency by optimizing the stator blades angles
- Authors: Popov G.M.1
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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
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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 of the Theory of Engine for Flying Vehicle Department
Russian FederationReferences
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