MULTIDISCIPLINARY ANALYSIS OF THE OPERATIONAL TEMPERATURE INCREASE OF TURBINE BLADES FOR AIRCRAFT ENGINE BY APPLICATION OF THE CERAMIC THERMAL BARRIER COATINGS ZrO2/20%Y2O3< |
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| G. L. Pintilei, D. S. Dragomir, L. A. Dragan, I. V. Crasmaru, A. C. Barbinta, C. Munteanu |
- Abstract:
- The improvement of the temperature resistance of the aircraft engine elements can be obtained by application of a ceramic coating, single layer (TBC) or several composite layers. Turbine blades are made of a super alloy that has a maximum operating temperature of close to 1000°C, the idea of using ceramic materials was foreseen. To increase thermal resistance of engine the elements requires, apart from laboratory investigations, also numerical study of the different aero-engine parts. For aircraft engine the most important are turbine blades, where high temperatures and stress concentrations during thermal shocks or thermal fatigue can be observed during engine exploitation.
The present paper deals with the solution of the transient temperature transfer problem in bare and thermal barrier coated alloy Inconel 625 for the temperature range up to 1000 ºC. The computational fluid dynamics (CFD) part of analysis was performed by application of ANSYS Fluent code receiving the temperature field of combustion gas. - Keywords:
- TBC, ANSYS, finite element
- Download:
- IMEKO-YSESM-2012-50.pdf
- DOI:
- -
- Event details
- IMEKO TC:
- TC15
- Event name:
- TC15 Youth Symposium 2012
- Title:
11th Youth Symposium on Experimental Solid Mechanics (TC15)
- Place:
- Brasov, ROMANIA
- Time:
- 30 May 2012 - 02 June 2012