Non-synchronous vibration simulation experiment table for blades and experiment operation method thereof

Abstract

The invention discloses a non-synchronous vibration simulation experiment table for blades and an experiment operation method of the experiment table, belonging to the field of aircraft engines. The experiment table comprises a pressure container, a jet cylinder, a pressure sensor supporting seat, an experiment plate supporting seat, a vibration exciter, an experiment table bed body and a platform supporting seat, wherein the pressure container is connected with the jet cylinder through a connecting pipeline; the jet cylinder is arranged at one end of the experiment table bed body; the vibration exciter is arranged at the other end of the experiment table bed body; the experiment plate supporting seat is arranged between the vibration exciter and the jet cylinder; the pressure sensor supporting seat is arranged between the experiment plate supporting seat and the jet cylinder; a vibration separating block and the platform supporting seat are arranged at the lower end of the experiment table bed body; and the experiment table bed body is connected with the platform supporting seat through the vibration separating block. According to the non-synchronous vibration simulation experiment table for blades, the distance between the jet cylinder and the experiment plate supporting seat can be adjusted; the experiment result is more accurate and effective through the vibration separating block; the pressure and speed of the jet air flow can be adjusted according to different needs of experiments; and the experiment plates can be replaced in the device.

Description

technical field [0001] The invention belongs to the field of aero-engines, and in particular relates to a blade asynchronous vibration simulation test bench and an test operation method. Background technique [0002] Since many compressor blades are used for a long time, serious damage will occur. The factor causing this phenomenon is the asynchronous vibration of the compressor blades. It is based on gas jet dynamics, combined with vortex theory, and achieves resonance by coupling with a flexible plate that simulates a blade. Under normal circumstances, the frequency of blade resonance is an integer multiple of the rotation frequency of the shaft where the blade is located, but in the experimental measurement, the frequency measured when the blade resonates is not an integer multiple of the rotation frequency of the shaft. Therefore, during the working process of the blade , a kind of airflow is produced, which affects the vibration of the blade. This airflow is the tip c...

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Problems solved by technology

When it hits the blade, it will generate a feedback sound wave. When the wavelength of this feedback sound wave is equal to the distance from the starting point of the tip clearance flow to the blade, it is considered that the tip clearance

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