Abstract
This paper conducts a coupled vibration analysis of a two-stage bladed disk rotor system. According to the finite element method, the bladed disk rotor system is established. The substructure modal synthesis super-element method (SMSM) with a fixed interface and free interface is presented to obtain the vibration behaviors of the rotor system. Then, the free vibration results are compared with the ones calculated by the cyclic symmetry analysis method to validate the analysis in this paper. The results show that the modes of the two-stage bladed disk not only include the modes of the first- and second-stage bladed disk, but also the coupled modes of the two-stage bladed disk.
Highlights
An aero-engine is a kind of high-speed rotating machinery with a complex structure
The dynamic frequency of the standard contact bladed disk system under the working speed was analyzed by using the cyclic symmetry analysis method and the modal synthesis superelement method of fixed interface prestressed and free interface substructures, respectively
It can be seen that compared with the cyclic symmetry analysis method, the maximum relative error of the dimensionless dynamic frequency of the modal synthesis super-element method of the prestressed free interface substructure with a fixed interface is 5.68%
Summary
An aero-engine is a kind of high-speed rotating machinery with a complex structure. The rotating blades and the fixed bladed disk are the important key parts of the aero-engine. The above works are mainly based on the finite element method to study the coupled modes and responses of the shaft–disk–blades system under the tuned and mistuned bladed disk. Using the fixed interface prestresselement method, based on the fin3iotf2e8 ele quency analysis of the first-stage blade modes of the multi-stage blade-disc system have not been studied, and the coupled model. Respectively using the substructure modal synthesis super-element method and the cyclic symmetry analysis method, two kinds of accurate finite element blade tenon and tenon grooves a model for two-stage bladed disk were established. Materials and Methods of the disk are as follow Using the fixed interface prestress-free interface substructure modal synthesis superratio μ = 0 .3 , density ρ =4640kg / element method, based on the finite element analysis software ANSYS, the dynamic frequency analysis of the first-stage bladed disk system of the compressor was carried out. The higher order modes of the main modes of the fixed interface are generally omitted, and only some of the lower order modes are taken, greatly reducing the scale of analysis and calculation
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