In the process of performance enhancement for a specific type of micro gas turbine

serious issues such as the deterioration of rotor dynamic characteristics and excessive overall vibration have emerged. There is an urgent need to develop a novel vibration control structure that can match the high-speed rotor system within confined spaces. This paper presents a performance enhancement solution for a rotor system of a specific micro gas turbine model. By modifying the structure and arrangement of the conventional integral squeeze film damper elastomer

the new elastomeric components are arranged circumferentially to meet the spatial constraints in the radial direction of the support points. This configuration enables the adjustment of the stiffness and damping of the support points for high-speed rotor systems within confined spaces. To validate the vibration control effectiveness of the newly designed circumferential integral squeeze film damper

this paper conducts a test with support points incorporating the circumferential integral squeeze film damper. The experimental results demonstrate that the maximum amplitude of the rotor is reduced by 65.6% with the implementation of the damper compared to the original support. The circumferential integral squeeze film damper effectively controls the vibration levels of the entire system under spatial constraints.