Thermomechanical Optimisation Of Fatigue Strength For Aircraft Engine Parts
Price
Free (open access)
Transaction
Volume
17
Pages
9
Published
1997
Size
706 kb
Paper DOI
10.2495/SURF970341
Copyright
WIT Press
Author(s)
P.D. Zhemanyuk, I.E. Kovalev, V.G. Mikhailutsa, S. A. Voitenko, F.P. Banas, A.P. Petrov & A.E. Kovalev
Abstract
Thermomechanical optimisation of fatigue strength for aircraft engine parts P. D. Zhemanyuk*, I. E. Kovalev\ V. G. Mikhailutsa*, S. A. Voitenko*, F. P. Banas\ A. P. Petrov\ A. E. Kovalev^ Moscow a^e^v^mA7-r^c^^ [/M/ Moscow, Russia The manufacturing process of compressor blades from heat-resistant double-phase titaniun alloy BT8M1 (Ti-5Al-4Mo-lSn-lZr) for Motor-Sich JSC turbo-shaft engine has been studied. The objective of study was definition of the manufacturing factors affe- cting the blades altering of resistance to fatigue and definition of critical points of the manufacturing process. The above mentioned blades are subjected under manufacture to three steps of cold plastic deformation with intermediate heat treatments in the following sequence: 1) primary forge-rolling, 2) high temperature annealing at 930° C, 3) the second forge-rolling, 4) low temperature annealing at 590° C, 5) surface hardening. Modelling of blade
Keywords