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Publikācija: Analysis of Repaired Gas Turbine and Compressor Blades

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Nosaukums oriģinālvalodā Analysis of Repaired Gas Turbine and Compressor Blades
Pētniecības nozare 2. Inženierzinātnes un tehnoloģijas
Pētniecības apakšnozare 2.1. Būvniecības un transporta inženierzinātnes
Autori Aleksandrs Tiškunovs
Sergejs Gluhih
Andris Popovs
Aleksandrs Korjakins
Atslēgas vārdi turbine blade, compressor blade, modelling, streams, internal cooling, damage simulation, material change, Von Mises equivalent stress, displacements, experiment, result comparison
Anotācija In order to reach desired levels of efficiency and power output of jet engines, advanced gas turbine and compressor blades made from Ti-6AL-4V alloy operate at very high temperatures (up to 600 ° C) and speeds (up to 10000 rpm). Pressure of springing streams and inertial forces are main reasons of stress appearance in the blades. Besides that, blade usually could be out of action after one’s edges had become damaged under temperature or foreign object hit negative influence. High cycle fatigue (HCF) accounts for 56 % of major aircraft engine failures and ultimately limits the service life of most critical rotating components. Extensive inspection and maintenance programs have been developed to detect, re new and replace defected blades, to avoid catastrophic engine failure. Various modern technologies including laser cladding (filling layers of sprayed material) allow prolongation of blades’ life by damaged part’s renovation with alternate material. The general aim of the present work concludes of blades’ mechanical bahavour comparison before and after renewal
DOI: 10.3846/1648-7788.2008.12.46-50
Atsauce Tiškunovs, A., Gluhih, S., Popovs, A., Korjakins, A. Analysis of Repaired Gas Turbine and Compressor Blades. Aviation, 2008, Vol.12, No.2, 46.-50.lpp. e-ISSN 1822-4180. ISSN 1648-7788. Pieejams: doi:10.3846/1648-7788.2008.12.46-50
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ID 3473