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About the thermal protection of the oil cavities for designing gas turbine engines
- Authors: Tryanov A.Y.1, Grishanov O.A.1, Vinogradov A.S.1
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Affiliations:
- Samara State Aerospace University
- Issue: Vol 8, No 3-1 (2009): Special Issue
- Pages: 318-328
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/715
- DOI: https://doi.org/10.18287/2541-7533-2009-0-3-1(19)-318-328
- ID: 715
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Abstract
The necessity of a effective thermal protection for a oil cavities in the air engines with the high temperature level is proved. For turbojet bypass engines the influence on the reliability of the following factors is shown. There are a choice of the turbine constructive scheme, a structure of cooling air flows inside the turbine and a the turbine oil cavity.
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About the authors
A. Ye. Tryanov
Samara State Aerospace University
Author for correspondence.
Email: vest@ssau.ru
Russian Federation
O. A. Grishanov
Samara State Aerospace University
Email: vest@ssau.ru
Russian Federation
A. S. Vinogradov
Samara State Aerospace University
Email: vest@ssau.ru
Russian Federation
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