Comprehensive Report on Materials for Gas Turbine Engine Components
Anushraj B1, Winowlin Jappes J T2, Adam Khan M3, Dillibabu V4, Brintha N C5
1Anushraj B, Centre for Surface Engineering, Department of Mechanical Engineering, Kalasalingam Academy of Research & Education, Virudhunagar (Tamil Nadu), India.
2Winowlin Jappes J T, Centre for Surface Engineering, Department of Mechanical Engineering, Kalasalingam Academy of Research & Education, Virudhunagar (Tamil Nadu), India.
3Adam Khan M, Centre for Surface Engineering, Department of Mechanical Engineering, Kalasalingam Academy of Research & Education, Virudhunagar (Tamil Nadu), India.
4Dillibabu V, Scientist, Small Turbo Fan Section, Gas Turbine Research Establishment (GTRE), DRDO, Bangalore (Karnataka), India.
5Brintha N C, Department of Computer Science and Engineering, Kalasalingam Academy of Research and Education, Virudhunagar (Tamil Nadu), India.
Manuscript received on 02 December 2019 | Revised Manuscript received on 14 December 2019 | Manuscript Published on 30 December 2019 | PP: 155-158 | Volume-9 Issue-2S2 December 2019 | Retrieval Number: B10361292S219/2019©BEIESP | DOI: 10.35940/ijitee.B1036.1292S219
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open-access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: In the past three decades, it is very challenging for the researchers to design and development a best gas turbine engine component. Engine component has to face different operating conditions at different working environments. Nickel based superalloys are the best material to design turbine components. Inconel 718, Inconel 617, Hastelloy, Monel and Udimet are the common material used for turbine components. Directional solidification is one of the conventional casting routes followed to develop turbine blades. It is also reported that the raw materials are heat treated / age hardened to enrich the desired properties of the material implementation. Accordingly they are highly susceptible to mechanical and thermal stresses while operating. The hot section of the turbine components will experience repeated thermal stress. The halides in the combination of sulfur, chlorides and vanadate are deposited as molten salt on the surface of the turbine blade. On prolonged exposure the surface of the turbine blade starts to peel as an oxide scale. Microscopic images are the supportive results to compare the surface morphology after complete oxidation / corrosion studies. The spectroscopic results are useful to identify the elemental analysis over oxides formed. The predominant oxides observed are NiO, Cr2O3, Fe2O3 and NiCr2O4. These oxides are vulnerable on prolonged exposure and according to PB ratio the passivation are very less. In recent research, the invention on nickel based superalloys turbine blades produced through other advanced manufacturing process is also compared. A summary was made through comparing the conventional material and advanced materials performance of turbine blade material for high temperature performance.
Keywords: Nickel, Corrosion, Oxide, SEM, EDS, XRD.
Scope of the Article: Materials Engineering