Faculty Publications

Now showing 1 - 3 of 3

Evaluation of functionally graded YSZ - IN625 clad without bond coat using laser directed energy deposition
(Elsevier B.V., 2023) Likhwar, J.; Thanumoorthy, R.S.; Bontha, S.; Balan, A.S.S.
M-CrAlY or M-Cr-based bond coats are used as a buffer layer to apply ceramic thermal barrier coatings (TBCs) to metal turbine blades. However, due to oxygen diffusion, thermally grown oxides grow over the bond coat material, leading to coating failure in the components. Therefore, this study attempts to fabricate a novel TBC-coated IN625 without bond coat material using a Functional grading approach. The findings from this study may pave the way for processing functionally graded ceramic materials using Laser Additive manufacturing techniques. This study also evaluates the performance of functional grading in joining dissimilar materials using small spot-size laser sources. In the present study, samples were fabricated for three sample conditions: S1: direct clad, S2: 25% linear grading, and S3: 50% linear grading. The interface between Yttria Stabilized Zirconia (YSZ) and IN625 for the S1 sample showed discontinuous and horizontal cracks along the interface due to steep variations in thermal properties. However, the interface of S2 and S3 samples showed good adhesion and a smooth transition in microstructure between IN625 and YSZ as a result of functional grading. SEM micrographs showed homogeneous YSZ distributions without segregation within the IN625 matrix. This was attributed to strong Marangoni flow as a result of the small spot-size laser beam used in this study. © 2023 Elsevier B.V.
Thermal life assessment of laser powder-directed energy deposited NiCrAlY/CuCrZr bimetallic clad for rocket nozzle applications
(Elsevier B.V., 2024) Thanumoorthy, R.S.; Urs, S.S.; Bontha, S.; Balan, A.S.S.
To enhance the thermal life of rocket exhaust nozzles, the hot side of copper liners is coated with thermal barrier coatings (TBCs) to provide thermal insulation and oxidation resistance. However, interface failures often occur between M-CrAlY bond coats and nozzle liners due to significant differences in their thermal expansion coefficients (CTE). This study explores the use of Laser Powder-Directed Energy Deposition (LP-DED) to clad NiCrAlY onto a CuCrZr substrate, as the process offers localized heating which can offer better bond strength. Optimization trials were conducted using single and multi-track studies to identify optimal parameters. Due to the low energy absorption of the CuCrZr substrate to 1070 nm laser sources, cladding was performed at a high energy density of 135 J/mm2 with a 1.2 g/min feed rate to achieve defect-free clads with sufficient diffusion. The bulk of the NiCrAlY clads showed ??-Ni3Al, ?-NiAl, and ?-Ni phases, while Y4Al2O9 and Y2O3 oxides formed on the top surface due to aluminum and yttrium depletion at high temperatures. The clads exhibited cellular dendritic microstructures at the bulk region, and planar microstructures were observed at the dilution zone. EBSD-KAM maps showed higher dislocation density near the interface due to CTE mismatch across substrate and clad. Scratch tests confirmed strong adhesion with no interface cracks, though crack propagation was observed from the edges after 50 isothermal cycles, driven by copper erosion. With Cu diffusion, interface region exhibited a graded microstructure which could enhance CTE, improving compatibility compared to standard NiCrAlY alloys. © 2024 Elsevier B.V.
A novel NiCrAlY-Cu based bond coat for rocket nozzle applications through LP-DED process
(Elsevier Ltd, 2025) Thanumoorthy, R.S.; Vijay, A.; Bontha, S.; Balan, A.S.S.
This study explores the development of a novel bond coat for copper-based substrates with the goal of minimizing thermal expansion mismatch and enhancing thermal life in rocket nozzle applications. The effect of copper (Cu) addition on the microstructure, phase evolution, and thermo-mechanical behavior of NiCrAlY clads fabricated via laser powder-directed energy deposition (LP-DED) is systematically investigated to optimize their performance. SEM and elemental mapping reveal a shift from columnar to cellular substructures with Cu additions up to 20 wt%, while higher Cu contents lead to coarse dendritic growth and Cu segregation at grain boundaries, inducing localized strain and crack formation. XRD and DFT analyses indicate that Cu suppresses the ?-NiAl phase and stabilizes the ?-Ni matrix due to its limited solubility in ? and preferential partitioning into ?. High-temperature XRD and EDS analyses show that while pure NiCrAlY forms a continuous alumina scale, Cu-enriched clads develop fragmented and crack-prone thermally grown oxides (TGOs), compromising the oxidation resistance. KAM analysis suggests reduced lattice strain at 10 wt% Cu, followed by increased dislocation density at higher concentrations. Thermal expansion measurements indicate a significant increase in the coefficient of thermal expansion (CTE) at 10 wt% Cu, improving compatibility with Cu-based substrates. However, further Cu additions yield minimal CTE benefits while degrading mechanical strength. Microhardness declines from ?406 Hv (0 % Cu) to ?251 Hv (40 % Cu) due to solid solution softening and ?-phase suppression. A radar plot comparing key metrics identifies 10 wt% Cu as the optimal composition, offering a balanced property set for regeneratively cooled rocket nozzle systems. © 2025 Elsevier B.V.

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