Finite Element Modeling of Contact Heat Transfer in the Turbine Rotor Design of an Aircraft Gas Turbine Engine
- 10.2991/aviaent-19.2019.38How to use a DOI?
- finite element method, contact problem, contact heat transfer, contact thermal resistance
On the basis of the finite element method (FEM) a mathematical model of the modular structure of the turbomachine exemplified by the aircraft gas turbine engine, AL-31F, is developed. It is notable for describing the solution of interdependent problems of the theory of elasticity and thermal conductivity, taking into account the changes in the parameters of the contact interaction of the turbomachine parts. A technique allowing obtaining updated values of stress and temperature fields in the modular structure of turbomachines, operating in a complicated complex of structural-force and thermal effects, is proposed with the identification of the influence of contact thermal resistance on the temperature field.
- © 2019, the Authors. Published by Atlantis Press.
- Open Access
- This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).
Cite this article
TY - CONF AU - A. Kudryavtsev AU - I. Zotov PY - 2019/11 DA - 2019/11 TI - Finite Element Modeling of Contact Heat Transfer in the Turbine Rotor Design of an Aircraft Gas Turbine Engine BT - Proceedings of the International Conference on Aviamechanical Engineering and Transport (AviaENT 2019) PB - Atlantis Press SP - 200 EP - 204 SN - 2352-5401 UR - https://doi.org/10.2991/aviaent-19.2019.38 DO - 10.2991/aviaent-19.2019.38 ID - Kudryavtsev2019/11 ER -