Construction development of a combined case and its dynamic strength calculation at breakage of the rotor blade
Aerospace propulsion engineering
1. United Engine Corporation “Saturn”, 163, Lenin av., Rybinsk, Yaroslavl region, 152903, Russia
2. United engine corporation (UEC), 16, Budyonny avenue, Moscow, 105118, Russia
Presented paper is devoted to solution to the problem of blade fragments localization during its accidental breakage with the help of proposed design of a combined case which consists of the metallic base and layer of untreated aramid yarns tightly wound on the metal substrate.
The main purpose is to prevent the combined case damage of aircraft structure dangling from the accident decayed fragments of the compressor including a torn shoulder blade or its fragment.
In the frame of this work a robust finite element combined case modeling methodology, in which there is an approach for modeling of winding impregnated aramid yarns, was created. Method for construction and configuration of computer system based on a three-dimensional code LS-DYNA, which provides authentic simulation of multi-layer composite materials used in protective systems for localization of engine broken blades, is implemented.
Developed numerical technology of calculation of structural elements dynamic deformation is verified by the results of field tests.
Keywords:combined case, impregnated aramid fabric, deformation, broken scapula, strength, armor protection, calculation, finite element method
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