Designing of the blades of aircraft propellers by the finite element method, taking into account the strength of structure

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The blades of contemporary turboprop engines have a complex spatial configuration. They can be classified as shells. Methods for the shells calculation are well known. A number of computer programs have been created on their basis. However, these programs do not take into account the peculiarities associated with the mutual influence of deformations of the blade and the aerodynamic and inertial loads acting on it. The aim of this work is to develop a method of finite element calculation of aircraft propeller blades taking into account aeroelastic effects and to create a computer program on its basis that is available to a wide range of designers and engineers. The finite element method is used in a geometrically nonlinear formulation. As the initial one, the equilibrium equation is used, which includes a complete nonlinear stiffness matrix and takes into account both conservative and non-conservative loads. The blade of one of the serial propellers was calculated. The effect of deformations on the magnitude of the aerodynamic load and, as a result, on the stresses in the design sections was found and analyzed. The proposed technique and the program compiled on its basis can be used in the design of aircraft propeller blades.

About the authors

Vladimir P. Agapov

National Research University (Moscow State University of Civil Engineering)

Author for correspondence.
SPIN-code: 2422-0104

Professor of the Department of Applied Mechanics and Mathematics, MGSU, Doctor of Technical Sciences

26 Yaroslavskoe Shosse, Moscow, 129337, Russian Federation

Kurban R. Aidemirov

Daghestan State Technical University

SPIN-code: 8167-4343

Associate Professor of the Department of Strength of Materials, Theoretical and Structural Mechanics, FSBEI HE “DSTU”, Candidate of Technical Sciences

70 I Shamilya Ave., Makhachkala 367026, Russian Federation


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Copyright (c) 2021 Agapov V.P., Aidemirov K.R.

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