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Seal designing in a structure of the cooling system in gas turbine engine
- Authors: Vinogradov A.S.1, Myatlev A.S.1
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Affiliations:
- Samara State Aerospace University
- Issue: Vol 8, No 3-1 (2009): Special Issue
- Pages: 217-221
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/699
- DOI: https://doi.org/10.18287/2541-7533-2009-0-3-1(19)-217-221
- ID: 699
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Abstract
The seal design influence on work of the secondary air system in gas turbine engine is shown. The design method of the such system with the definition of mutual influence of gas seal and radial gap change is generated. This methods and means for practical realization are recommended at the engine design.
About the authors
A. S. Vinogradov
Samara State Aerospace University
Author for correspondence.
Email: vest@ssau.ru
Russian Federation
A. S. Myatlev
Samara State Aerospace University
Email: vest@ssau.ru
Russian Federation
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