Research The Modified Aero-engine Turbine Blade Bumps Rubs Analysis And The Quality Improvement

Aero Engines is a thermal machine which have to bear harsh pneumatic and mechanical loads, and to require long-term reliable operation, it is also a complex system composed of many parts and accessories, and its reliability directly affects flight safety, it is not only affecting longevity engine but also the engine maintenance costs and logistics support. The turbine blades are one of the main components affecting the reliability and longevity of aviation engines, and its structure a nd carrying cases are very complex, and the working environment is very bad for bearing curved centrifugal force and centrifugal moment, centrifugal rotation torque, axial force and torque generated by aerodynamic forces, but also withstanding the thermal stress caused by temperature variations and vibration loads and so on. In this paper, by using a modified aero-engine turbine rotor and stator blades rubbing for the object, the fault mechanism analysis and quality improvement research are carried out, th e main research work is as follows:First, this paper describes a modified system aeroengine turbine stator blades rubbing turn the status quo, starting with different inspections and analysis methods from the turbine blade rubbing faulty, by using UG mode ling and line elastic finite element stress analysis, the strength calculation is carried out, faulty hazards is analyzed after using binocular glass magnifier and differential metering analysis.Second, on the basis of metallurgical test results and the s tucture, the outside objects falling reason of catching wear is excluded by analysising chemical composition, hardness, microstructure, metallurgy and fracture energy spectrum results, of physical and chemical results were analyzed. After the detailed anal ysis and calculation of the hot and cold states size, and the comparion of the structure variation, the true reason for rubbing of guide vane and work blade leading edge is design flaws.Third, for a modified design flaws aeroengine turbine cooling flow pa th, developed three quality improvement programs. By considering the implementation of the workload, ease, economy, foreign field use impact, the second and third methods are chosen to solve this major faulty and ensure the outfield engines safty.In this paper, through the fault case analysis, theoretical calculations and experimental verification of quality improvement, there is a preliminary exploration for rubbing failture of turbine rotor and stator blades, the quality improvement and modification research direction is provided.