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Причины повреждения последней ступени компрессора мощной газотурбинной установки
Abstract
The article presents a design analysis of possible reasons of crack generation in peripheral sections of blades on the last compressor stage in powerful gas turbine units. It shows the possibility of reducing dynamic stress under operating conditions by means of local reshaping of blade peripheral sections, which causes only negligible increasing of aerodynamic losses.
About the Authors
V. G. Gribin
НИУ «МЭИ»
Russian Federation
Russian Federation
M. V. Pastukhova
НИУ «МЭИ»
Russian Federation
Russian Federation
References
1. Alsina A., Tip corner cracking: Root cause analysis, IMechE CP 2002
2. Kern G. Risk of corner crack in compressor blading. International Journal of Rotating Machinery, 2002, vol.3, No.3.
3. Buehler S. Compressor blade tip corner cracks field study summary. ASME, 2004.
4. Костюк А.Г. Динамика и прочность турбомашин. М.: МЭИ, 2007.
Review
For citations:
Gribin V.G., Pastukhova M.V. . Safety and Reliability of Power Industry. 2012;(4(19)):27-30. (In Russ.)
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