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Blade vibration response analysis method based on fluid-solid interaction

A fluid-solid coupling and vibration response technology, applied in the field of aviation systems, can solve problems such as high computational cost and huge computational load, and achieve considerable application prospects, improve computational efficiency, and wide applicability

Pending Publication Date: 2020-08-11
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, the working environment of the engine blade is a complex unsteady flow field. Analyzing the vibration response of the blade is a fluid-solid coupling problem. Completely solving the solid and fluid equations to calculate the exact solution of the blade vibration response is a huge amount of calculation. costly work

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  • Blade vibration response analysis method based on fluid-solid interaction
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  • Blade vibration response analysis method based on fluid-solid interaction

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Embodiment Construction

[0029] The present invention will be further described below in conjunction with the accompanying drawings.

[0030] For the blade model in a certain type of engine compressor, a 1.5-level three-row (front row stator, rotor and rear row stator) single-channel sector flow field calculation model is established, as shown in figure 2 The number of blades in each row is shown in Table 1.

[0031] Table 1 Number of leaf rows

[0032]

[0033] First, the nonlinear harmonic method is used to analyze the unsteady flow field in the blade flow channel to obtain the unsteady load on the blade surface, and the Fourier transform is used to analyze the frequency spectrum of the unsteady results. , extract the first few key frequencies and corresponding loads with larger amplitudes to simulate the original flow field, and obtain the aerodynamic excitation force on the blade surface through the fluid-solid coupling interface program.

[0034] For unsteady calculation, set the inlet tota...

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Abstract

The invention discloses a blade vibration response analysis method based on fluid-solid interaction. The blade vibration response analysis method comprises the following steps of: firstly, carrying out unsteady analysis on a flow field in a blade flow channel by adopting a nonlinear harmonic method to obtain unsteady load distribution on the surface of a blade, and extracting a load correspondingto a key frequency by adopting Fourier transform to obtain a pneumatic exciting force borne by the blade; secondly, carrying out fluid-solid interaction analysis on the blade and the flow field in theflow channel of the blade, analyzing aerodynamic work applied to the blade by the aerodynamic force when the blade vibrates, and acquiring modal aerodynamic damping ratios of all orders of vibrationof the blade in the flow field according to an energy equivalence principle; and finally, loading the aerodynamic exciting force and the modal aerodynamic damping ratio of each order onto the blade, and performing vibration response analysis on the blade by adopting a modal superposition method. The blade vibration response analysis method can efficiently and accurately analyze the vibration response of the blade under the action of the unsteady aerodynamic force, and provides support for the safety guarantee and design work of an engine.

Description

technical field [0001] The invention relates to the technical field of aviation systems, and mainly relates to a blade vibration response analysis method based on fluid-solid coupling. Background technique [0002] With the development of modern aircraft, people have higher requirements for aero-engines. On the one hand, they require large thrust, high thrust-to-weight ratio, and low fuel consumption. On the other hand, they require high reliability, long life, and light weight. . At present, the use of various new technologies has improved the boosting ratio and efficiency of the compressor, but the aerodynamic load on the surface of the compressor blade has greatly increased, and the vibration of the blade is serious, which in turn causes the high cycle fatigue failure (HCF) of the blade. Once the blade breaks and fails, the fragments may damage other blades or even penetrate the casing, thereby seriously damaging the engine and even causing flight accidents. [0003] In...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/28G06F119/14G06F119/02
CPCG06F30/17G06F30/28G06F2119/14G06F2119/02Y02T90/00
Inventor 漆文凯许正华田少杰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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