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Effect of Blade-Casing Rub Event on Blade, Casing and Turbine Shaft in Gas Turbine Engine

Harisha S.K, Shivaraj Kumar D.N., Ramachandra. K, Narendra Babu K.


Numerical results obtained for an Inconel-718 compressor blade rubbing a stationary casing of gas turbine at engine speed are described in this paper. Higher performances of gas turbine depend on minimum clearance between rotating blade and stationary casing. But tighter clearances result in rub event at blade tips, transferring load on different parts of gas turbine in radial, axial and tangential directions. The axial, radial and circumferential loads are noted for sudden incursions of varying severity, defined by incursion depths ranging from 0.02 to 0.7 mm. The effect of casing and blade tip rub forces being transmitted to the shaft are analyzed in terms of the dynamic stability of the rotor. The obtained results describe the transient dynamics of rotor and casing at engine operational speed of 10,000 rpm. On higher incursion the maximum circumferential load increases significantly, while the maximum axial load increases much less, demonstrating the non-linear nature of the rub phenomena. The stress-effective, deformation and temperature at the blade tip are simulated. The results are obtained using DEFORM software and compared with LS-DYNA solver.

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Harisha SK, Shivaraj Kumar DN, Ramachandra K et al. Effect of Blade-Casing Rub Event on Blade, Casing and Turbine Shaft in Gas Turbine Engine. Trends in Mechanical Engineering & Technology. 2016; 6(1): 43–54p.


Gas turbine blade, casing, shaft, rub, load, deformation

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