Research On Typical Fault Treatment Method Of Turbomachinery

Turbomachinery is a highly complex and sophisticated powered fluid machinery,which is widely used in industrial fields such as aero-engines and gas turbines.Excessive vibration,seal leakage and blade failure are typical faults of turbomachinery,which will seriously affect the safe and stable operation of turbomachinery.Therefore,it is necessary to study the typical fault management methods of turbomachinery.In this paper,the turbomachinery vibration exceeds the standard,seal leakage and blade failure of three typical fault management methods to study.The specific contents are as follows.1.Aiming at the problem that the vibration of the centrifugal impeller of the compressor exceeds the standard when a micro turbojet engine passes through the first-order critical speed,the integral squeeze film damper(ISFD)technology is proposed to control the rotor vibration.According to the structure and assembly characteristics of the engine rotor bearing chock,a J-type ISFD was designed.The dynamic numerical calculation method of ISFD was studied.The research on the static and dynamic characteristics of ISFD was carried out.The influence of different oil supply pressure and oil viscosity on the damping characteristics of ISFD was analyzed,which lays a theoretical foundation for the application of ISFD in rotor system.2.According to the structural characteristics of the micro turbojet engine rotor system,the rotor dynamic model of the engine rotor system was established to explore the dynamic influence of ISFD on the rotor system.The vibration reduction experiment of a single-disc cantilever rotor system based on ISFD is carried out.Under various unbalance and speed conditions,ISFD can effectively reduce the unbalanced vibration of the rotor system.The whole engine rotor system test based on ISFD is carried out,and the vibration speed can be reduced by more than 50%,which provides a certain engineering application reference for the vibration control of turbomachinery rotor.3.In view of the eccentricity problem of labyrinth seal and honeycomb seal in the operation of turbomachinery,the radial and angular eccentricity adjustment scheme was designed.The high-speed rotating gas seal test device was built to simulate the radial eccentricity and angular eccentricity of different gas seals.The experimental study on the leakage characteristics of gas seals with different structures was carried out.The sealing mechanism and flow characteristics of different gas seals were explored.The influence of different installation errors on the leakage characteristics of seals was analyzed,which provides theoretical and experimental support for the design and optimization of labyrinth seal and honeycomb seal of turbomachinery.4.Aiming at the bending deformation fault of the second stage rotor blade of a gas turbine compressor,the blade profile is obtained by three-dimensional scanning technology and the modal analysis of the blade was carried out.The blade modal test bench was built to obtain the actual modal of the blade and verify with the simulation results.Subsequently,the operating monitoring data of the gas turbine was combined to determine the causes of blade fault and proposed several solutions to provide theoretical support for the maintenance and operation of the gas turbine.In summary,the research achievements of this thesis provide effective solutions and ideas for the treatment of typical faults of turbomachinery,effectively improves the stability of turbomachinery,and provides theoretical and technical support for the safe,stable and efficient operation of turbomachinery.