Research On Machining Technology For High-pressure Turbine Rear Axle

With the continuous development of aviation technology,parts and components of aeroengine have become increasingly complicated and difficult to process.The high-pressure turbine rear axle is an important transmission component,the quality of which directly affects the performance of the aeroengine.Due to the complex structure,thin-wall characteristic,ductility and high processing precision requirement of the high-pressure turbine rear axle parts,the processing quality is usually unstable.In addition,the part material is superalloy,which could lead to poor cutting performance,high cutting temperature,low machining efficiency,large tool loss,and low surface quality.In this paper,the processing technology of high-pressure turbine rear axle is studied to improve the quality stability and energy efficiency of parts processing.By analyzing the structure and material characteristics of the rear axle of high-pressure turbine,the processing bottleneck is clarified.Aiming at solving the machining process problem of parts,the processing technology of aeroengine high-pressure turbine rear axle parts is improved.The main research contents are as follows:(1)The structure and material characteristics of the high-pressure turbine rear axle are analyzed.The problems existing in the original processing route are solved with an introduction of the turning-milling combined machining technology in the finishing stage.A staged processing route is formed.The new route shortens the original 42 processes to 27 processes,and the processing cycle is significantly reduced,which can reduce the machining error of parts caused by multiple clamping positions.(2)With the rigidity analysis of the processing system,the parameters of the part fixture and processing tooling are determined.According to the actual production site,the processing equipment is selected.Special fixtures for parts is designed,the clamping position and clamping method are optimized,which reduces the deformation of parts by axial compression.A small T-milling cutter is designed for the inner bore groove structure of the high-pressure turbine.Through the processing test,the selected machine tools,fixtures and tools can meet the processing requirements of the parts.(3)According to the structure of the high-pressure turbine rear axle parts,the finishing turning trajectory and the milling trajectory are selective analyzed.Through the test and analyze of the parameters of the inner hole slot milling,the optimal machining parameters are determined.For the small deep hole drilling technology with large aspect ratio,the existing problems of traditional processing schemes are analyzed,gun drilling processing technology are introduced,and the optimal processing parameters are selected through cutting test.Through the research of this paper,the machining process of aeroengine high-pressure turbine rear axle parts is improved.The turning-milling combined machining technology and gun drilling technology are introduced,special fixtures and tools are designed.The turning and milling integrated processing of high-pressure turbine rear axle parts is realized and the quality problem of small deep hole is solved,which overcome the bottleneck of parts processing,streamline the parts processing process,shorten the part processing cycle,ensure the production and delivery of parts,and provide reference for the subsequent processing of the same type of parts.