For the new generation of high-performance aviation engines and Control Moment Gyroscopes (CMGs), this equipment is characterized by high speed, heavy load, high temperature, and lightweight. Relying solely on bearings is already difficult to meet its support and vibration reduction requirements. Therefore, squeeze film dampers have been proposed and widely used to control the vibration and stability of rotor systems. However, there is still a lack of detailed theoretical basis for the coupling mechanism between elastic ring deformation and oil film pressure, as well as the influence of elastic ring structural parameters on oil film pressure distribution. This article will conduct theoretical analysis and numerical simulation to address the above issues, and the research results will provide a theoretical basis for engineering design.