Investigation of Computational Techniques Efficiency in Thermal Stress Analysis of an Aircraft Turbine Exhaust Frame

Аuthors

Ryabov A. A.^1*, Zhelezov S. A.^2**, Rechkin V. N.², Shmotin Y. N.^3***, Veselov A. V.⁴, Muller A. ^5****

1. Sarov Engineering Center, Science and technology park "Sarov", 3, Parkovaya str., Satis, Nizhny Novgorod region, 607328, Russia
2. ,
3. United engine corporation (UEC), 16, Budyonny avenue, Moscow, 105118, Russia
4. United Engine Corporation “Saturn”, 163, Lenin av., Rybinsk, Yaroslavl region, 152903, Russia
5. CD-adapco (USA),

*e-mail: alex.ryabov@saec.ru
**e-mail: zhelezov@saec.ru
***e-mail: yuri.shmotin@npo-saturn.ru
****e-mail: alan.mueller@us.cd-adapco.com

Abstract

Comparison of Finite Element (Abaqus) and Finite Volume (STAR CCM+) computational techniques efficiency in investigation of an Aircraft Turbine Exhaust Frame thermal stress is being performed. Basic characteristic features, meshing efforts, numerical calculations results accuracy and convergence are being studied. Advantages of STAR CCM+ novel computational technique that can improve calculation efficiency and essentially reduce development effort are being demonstrated.

Keywords:

turbine Exhaust Frame (TEF); computational technique; finite element method; finite volume method; numerical calculations; mode of deformation.

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