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Theoretical definition of temperature fields at thermoplastic hardening of details of gas turbine engines
- Authors: Barvinok V.A.1, Vishnyakov M.A.1, Ignatiev S.A.1
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Affiliations:
- Samara State Aerospace University
- Issue: Vol 8, No 3-1 (2009): Special Issue
- Pages: 253-259
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/705
- DOI: https://doi.org/10.18287/2541-7533-2009-0-3-1(19)-253-259
- ID: 705
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Abstract
In work the technique of theoretical definition of temperature fields at thermoplastic hardening is presented. As an example results of calculations for unilateral cooling of a large-sized detail of type of a disk of the turbine of gas turbine engines are shown. Comparison of settlement and experimental temperature fields is resulted.
About the authors
V. A. Barvinok
Samara State Aerospace University
Author for correspondence.
Email: vest@ssau.ru
Russian Federation
M. A. Vishnyakov
Samara State Aerospace University
Email: vest@ssau.ru
Russian Federation
S. A. Ignatiev
Samara State Aerospace University
Email: vest@ssau.ru
Russian Federation
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