Study On The Scratches & Wears And Heat Transfer Of Gas Turbine Blade Tips On Aero-engines

Blade tips clearances control on Aero-engines is a very important section for polishing up pneumatic performances of aero-engines,and improving the efficiency of engines.In the high-speed rotation process of blades,the scratches and wears between blades and external rings are made possibly,because the heat expansion characteristics of blades and engine frame are not in accordance with each other.When turbine blade tips scratch with ceramic coatings of internal rings,the energies resulting from scratches and wears transfer into heat mostly,which heats the scratches zone up,can have an impact on the performance of blades badly.In the working process of aero-engines,scratches and wears can make the turbine blades in the periodic state of high-low temperature frequently,which could generate biggish residual stress around the vicinity of blades,and result in blade cracks even fractures which can bring aero-engines faults.This thesis conducted a scraping test and surface emissivity test,and the test data are detailed analysis,fitting empirical formula of temperature,scraping force and heat;numerical simulation of the flow field,the various factors in the process of scraping(leaf tip line speed,scraping and grinding the speed and quantity of scraping)effect on heat generation,analysis and comparison of the experimental and numerical calculation results of the conclusion..Through this study,in order to obtain high pressure turbine blades provide important theoretical basis for the transient temperature characteristics and the ceramic coating scraping process and stress characteristics;also calculates data rich database structure design and performance of aero engine test data and data,provide technical support and technical reserves for the research and a new generation of aviation the ground gas turbine engine and gas turbine blade tip scraping and heat transfer analysis.