COMPUTER MODELLING OF SHOCK INTERACTION OF THE LARGE BIRD WITH HIGH BYPASS RATIO TURBOFAN FAN BLADES

В. М. Меркулов, А. В. Шереметьев, А. В. Петров, Р. П. Придорожный, В. В. Донченко

Abstract


As a result of the experimental-calculated analysis, and the analysis of consequences of real cases of collision with large birds domestic and foreign high bypass ratio turbofans, the calculated model of shock interaction of a large bird with high bypass ratio turbofan fan blades is offered and its verification is spent. With use of the chosen model computer modelling of process and consequences of a large bird impact to the modern high bypass ratio turbofan with wide horde shroudless fan blades is led. The methodical approach by definition of degree of danger to the engine of consequences of collision with a large bird is offered.

Keywords


computer modelling, shock interaction, high bypass ratio turbofan fan blades, a large bird, experiment-calculated analysis, calculated model, verification, degree of danger to the engine, similarity of the design

References


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DOI: https://doi.org/10.32620/aktt.2017.7.11