This paper describes the blade containment tests for six sets of single model blade on a vertical breaking down tester with excess revolution.The experimental results indicate that the blade body fragment flying off i...This paper describes the blade containment tests for six sets of single model blade on a vertical breaking down tester with excess revolution.The experimental results indicate that the blade body fragment flying off impacts against the model aeroengine case time and again.The incident angle of the blade fragment against the case in the initial impact is smaller than in the later impacts,the case damage of the first impact is smaller than that of the final impact,and the impacts of the blade fragment against the case make the blade fragment crimple.In principle the experimental results of the blade fragment containment and non containment are consistent with the containment curve of single compressor blade (for use only in case of the blade body) in the Spey MK202 Stressing Standards (EGD 3) and are on the safe side.It is the preliminary conclusion that the containment curve of single compressor blade (for use only in case of the blade body) in EGD 3 can be used to predict the containment of the similar blade.展开更多
A LCF(Low Cycle Fatigue)test of a single rotor disk of a compressor is presented.The experimental results show that the location and the growth orientation of LCF crack in 9th single rotor disk reproduce those in the ...A LCF(Low Cycle Fatigue)test of a single rotor disk of a compressor is presented.The experimental results show that the location and the growth orientation of LCF crack in 9th single rotor disk reproduce those in the global compressor rotor.In addition,the LCF tests of the smooth round bar specimens are accompanied with the LCF tests of a single rotor disk,so as to estimate of the strain history of the eccentric holes in the disk.The statistical data of smooth round bar specimens tested to failure enables to estimate the LCF life to crack initiation for the eccentric holes in the disk of the global compressor rotor.展开更多
文摘This paper describes the blade containment tests for six sets of single model blade on a vertical breaking down tester with excess revolution.The experimental results indicate that the blade body fragment flying off impacts against the model aeroengine case time and again.The incident angle of the blade fragment against the case in the initial impact is smaller than in the later impacts,the case damage of the first impact is smaller than that of the final impact,and the impacts of the blade fragment against the case make the blade fragment crimple.In principle the experimental results of the blade fragment containment and non containment are consistent with the containment curve of single compressor blade (for use only in case of the blade body) in the Spey MK202 Stressing Standards (EGD 3) and are on the safe side.It is the preliminary conclusion that the containment curve of single compressor blade (for use only in case of the blade body) in EGD 3 can be used to predict the containment of the similar blade.
文摘A LCF(Low Cycle Fatigue)test of a single rotor disk of a compressor is presented.The experimental results show that the location and the growth orientation of LCF crack in 9th single rotor disk reproduce those in the global compressor rotor.In addition,the LCF tests of the smooth round bar specimens are accompanied with the LCF tests of a single rotor disk,so as to estimate of the strain history of the eccentric holes in the disk.The statistical data of smooth round bar specimens tested to failure enables to estimate the LCF life to crack initiation for the eccentric holes in the disk of the global compressor rotor.
