ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Forward slip compensation method for designing rolling mold cavity of compressor blade
Received date: 2016-03-01
Revised date: 2016-04-08
Online published: 2016-04-18
Supported by
National Natural Science Foundation of China (51475374,51505387); the Fundamental Research Funds for the Central Universities (3102015ZY087)
Rolling cavity is the key of rolling allowance free blade, Forward slip occurs in rolling process of high-pressure compressor blade, which cause a deviation of formed blade along rolling direction, so forward slip compensation need to be considered in designing mold cavity to improve the stacking height precision of blade. Contraposing forward slip phenomenon in rolling blade, the paper proposes and researches the optimum designing method which based on forward slip compensation for mold cavity of rolling compressor blade. Firstly, based on the analysis of cause and forward slip representation of rolling blade, the forward slip compensation mechanism is studied and a compensation model, namely, relationship between roller's central angle and stack height of section is proposed. After that, a set of sections which characterized the process mold is drawn, forward slip value of every section is calculated, and relationship between roller's central angle and stack height of section is set up. Then, based on the adjusted central angle, sector mapping algorithm in space for section curves is proposed and section curves are mapped; the rolling cavity surface through mapped section curves is reconstituted. Finally, an effective numerical calculation method is used to compare the stacking height of blade formed by forward slip compensated cavity and geometric cavity. The results show that optimized design of mold cavity can accurately control the blade forming accuracy of compressor blade in stack axis direction.
JIN Qichao , WANG Wenhu , JIANG Ruisong , ZHAO Dezhong , CUI Kang , XIONG Yifeng . Forward slip compensation method for designing rolling mold cavity of compressor blade[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(1) : 420173 -420173 . DOI: 10.7527/S1000-6893.2016.0117
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