Method for optimizing mass and size characteristics of a high-pressure turbine disk

Abstract


The article presents the results of weight and size optimization of a high-pressure turbine working disk for an augmented turbofan. The issues of modeling the operation of the engine’s first stage with a cover plate providing the delivery of cooling air to the blades are considered. Strength calculation of the stresses arising from the action of centrifugal forces under high-temperature conditions was carried out. A three-dimensional model of the disc was obtained. The finite element method was used. The pattern of temperature distribution in the disk body was obtained on the basis of heat calculation.  Based on the strength calculation, the stresses and strains of the turbine disk were determined.  Maximum stresses in the disc are located at the junction of the disc frontal area and the cooling air feed holes. Plastic deformation is observed in the area of the cavities for cooling air feed. It is shown that the stepped part of the disc should be made of a material with lower heat resistance and a higher value of permissible limit stress. Based on the study, a bimetallic disk design made by powder metallurgy was proposed.


About the authors

M. V. Siluyanova

Moscow Aviation Institute (National Research University)

Author for correspondence.
Email: dc2mati@yandex.ru

Russian Federation

Doctor of Science (Engineering), Professor

A. N. Grunin

Moscow Aviation Institute (National Research University)

Email: grunin.anton@mail.ru

Russian Federation

Postgraduate Student

A. D. Alendar

Moscow Aviation Institute (National Research University)

Email: artem.alendar@mail.ru

Russian Federation

Postgraduate Student

S. K. Kandaurov

Moscow Aviation Institute (National Research University)

Email: sergey@kbbase.ru

Russian Federation

Postgraduate Student

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