DAMPING FRAME MECHANISM FOR AXIAL COMPRESSORS

Abstract

The invention proposes a damping frame mechanism for the axial compressor of a jet engine, located at the bearing position in the compressor chamber. The mechanism comprises a thin-walled flexible bearing frame directly connected between the outer ring of the compressor bearing and the lower ring of the first-stage compressor stator, where the bending geometry of the frame body is designed to actively adjust the equivalent stiffness of the bearing through parameters such as the bending angle α and frame thickness t. Thanks to this elastic property, the mechanism is capable of absorbing the bending vibrations of the rotor, shifting resonance points out of the operating speed range and improving the overall dynamic characteristics. The damping frame has a compact axial structure, allowing direct installation between two adjacent compressor stages without increasing the engine length, and simultaneously integrates the lubrication piping system, oil distribution ring, and a mounting location for the bearing temperature sensor.The invention is suitable for application in aviation jet engines and small to medium-sized gas turbines requiring high efficiency, vibration stability, and optimized installation space.

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