Abstract The finite-difference method acceptable for on-board computers is applied to analyze the thermo-stressed state for the thermal-barrier coating of a perforated turbine blade and its wall at transient and stationary conditions of air-breathing jet engine operation during a flight.
Thermostressed state in turbine rotor blades with thermal barrier coating at transient conditions of air breathing jet engine operation
Russian Aeronautics (Iz VUZ) ; 56 , 4 ; 372-378
2013-10-01
7 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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