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- Title
某燃气轮机压气机叶片振动特性研究.
- Authors
张亮; 初曙光; 来亮; 王廷
- Abstract
For the failure of the compressor blade in a gas turbine, the vibration analysis of the compressor blade under disc coupled structure is performed through theoretical calculation and experimental.Through the use of the cyclic symmetry function and the contact function of the ANSYS WORKBENCH, a computational analysis on vibration of the blade disc in low compressor has been conducted.During the calculation, the effect has been taken into account of the rotating centrifugal force and temperature-dependent material parameters on the dynamic frequency characteristic of the blade.The resonance rotational speed obtained by Campbell diagram is 6 900 r/min.Then, vibration testing on the failed rotor blade under the whole gas turbine running has been completed by using non-contact microwave method.The resonance rotational speed obtained through the method is 6 988 r/min.The results show that the obtained harmonic resonance rotational speed is found to be in agreement with the theoretical calculation results, providing useful foundation for further failure analysis.
- Publication
Journal of Engineering for Thermal Energy & Power / Reneng Dongli Gongcheng, 2019, Vol 34, Issue 1, p34
- ISSN
1001-2060
- Publication type
Article
- DOI
10.16146/j.cnki.rndlgc.2019.01.006