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《Journal of Shenyang Aerospace University》 2016-01
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Analysis of working blade crack failure and optimal scheme for engine high pressure turbine

MA Li;TAN Wei;XUE Qing-zeng;Engine Affairs Military Representatives Office of Navy in Shenyang;Airplane Teaching and Research Section,Naval Aviation Academy;  
Working blade crack of high pressure turbine is common failure form of rotary component. Based on flight data identification and disassembly and examination,the cause of fault was analyzed,optimal design scheme was presented,and feasibility of optimal scheme was validated by experiment. Results indicate that under the optimal design scheme,minimum fatigue extreme increases from 138 MPa to 190 MPa with less influence on blade temperature,and negative effect of stress focus of blade film hole reduces.
【CateGory Index】: V263.6
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