Innovative deposition techniques that leverage the unique characteristics of yttrium aluminum garnet (YAG) are enabling realization of this material’s performance advantages as a thermal-barrier coating at ultrahigh temperatures.
Yttria-stabilized zirconia (YSZ) has long been the state-of-the-art thermal-barrier coating (TBC) material for gas turbine-engine applications. But as turbine inlet gas temperatures are pushed to new highs, YSZ is rapidly approaching its intrinsic limits. Despite outstanding properties that have kept this material at the forefront of gas-turbine technology for more than three decades, YSZ is only stable up to 1200°C (2192°F) – limiting maximum turbine operating temperatures. Advanced TBC materials are needed to support the higher firing temperatures of next-generation gas turbines.
One promising material system is yttrium aluminum garnet (YAG), which is thermally stable up to its melting point of 1970°C (3578°F). Thus far, manufacturing challenges have prevented the commercialization of YAG coatings for gas-turbine applications. However, new research funded by the U.S. Department of Energy’s Advanced Manufacturing Office (AMO) may soon overcome these barriers.
Project partners Solar Turbines Inc. (Solar) and Solution Spray Technologies LLC (SST) are applying an innovative deposition technique called solution precursor plasma spray (SPPS) that provides greater control over crystal structure and porosity compared to existing powder-based techniques. The project is demonstrating that the SPPS technique for YAG, previously demonstrated in a laboratory setting, can be successfully scaled to full-scale gas-turbine components.
Thermal-Barrier Coatings for High-Temperature Industrial Turbines
Industrial gas turbines are widely used in oil and gas, power generation and combined heat and power (CHP) applications to provide electric power, heat, gas compression and mechanical drive. To remain competitive, turbine efficiency improvements – along with emissions reductions – are a high priority.
Increasing the operating temperature is the most direct way to improve a turbine’s power density, but higher temperatures can also reduce component durability. Considering that modern gas-turbine engines operate at temperatures exceeding the melting point of state-of-the-art superalloys, thermal-barrier coatings (TBCs) play an essential role in insulating metal turbine components from hot gases.
While numerous ceramic materials have been proposed as high-temperature TBCs for gas turbines, only a few have been commercialized to date given the stringent application requirements. In addition to extreme temperatures, conditions in the hot section of a gas turbine also include an oxidizing environment, high pressures and high-velocity gas flows that can contain erosive and corrosive contaminants.
One particularly aggressive family of contaminants are the low-melting-temperature silicates, which include sand, dust and ash particulates. At gas temperatures beyond 1200°C, these materials begin to melt, forming glassy deposits of calcium magnesium aluminosilicate (CMAS) that can infiltrate into the porous structure of a TBC, inducing damaging thermal stresses.
Table 1 compares properties of three different TBC systems. The dominant TBC material in commercial turbine installations today is 7-8 wt.% yttria-stabilized zirconia (YSZ). While YSZ has a low thermal conductivity and high fracture toughness, its major limitation is its maximum operational temperature of 1200°C. Beyond this temperature, YSZ begins to destabilize and sinter. YSZ is also vulnerable to attack by molten CMAS, which can infiltrate and even partially dissolve the coating. One alternative to YSZ that has been adopted at higher temperatures is gadolinium zirconate (GZO). However, drawbacks of GZO include low fracture toughness, poor erosion resistance and high cost.
Yttrium aluminum garnet (YAG) has been less extensively studied than other systems partly because early research showed that conventional deposition techniques yielded an undesirable amorphous or semi-amorphous structure with poor durability.¹ However, YAG’s attractive properties, including thermal stability up to 1970°C and a thermal conductivity that decreases with increasing temperature, have stimulated renewed exploration.
This project is focused on overcoming manufacturing challenges to harness the performance advantages of YAG, supporting a step-change advancement in gas-turbine engine firing temperature and energy efficiency.
A New Deposition Method for YAG
The state-of-the-art air plasma spray (APS) process is the primary application method for TBCs at Solar. In the APS process, a powder is injected into a plasma plume, and molten particles are deposited onto the surface as “splats” (i.e., pancake-shaped lamellae) to build up the coating.
Unfortunately, this process is not viable for YAG, which does not form robust coatings from powder. But a novel technique called solution precursor plasma spray (SPPS, see sidebar) has shown new promise. Drawing from a liquid precursor rather than powder, SPPS enables deposition of YAG in the high-performance crystalline garnet phase. At laboratory scale, researchers from SST have demonstrated that SPPS YAG coatings can meet or exceed the performance of state-of-the-art YSZ for thermal conductivity, CMAS resistance, thermal-cycling durability and erosion resistance.¹
Solar is now collaborating with SST to transfer SPPS technology to a production setting, an effort that has included process development to overcome technical challenges associated with scale-up. For example, a 70% improvement in deposition rate was achieved by incorporating a higher-enthalpy plasma torch into the setup.
The project team was also able to increase the coating application distance by 50%, resolving a concern with the SPPS process for large and complex parts. Ultimately, successful process scale-up was validated through laboratory testing and rig testing of YAG-coated fuel-nozzle components (Fig. 1). Following rig testing, the nozzles were confirmed in good condition, and measurements of backside temperature demonstrated the insulating capability of the coating.
Higher TBC Performance through Application-Specific Microstructures
A key benefit of the SPPS process is the high level of process control. Process parameters can be tailored to achieve different microstructural features and levels of porosity. Figure 2 illustrates the range of microstructural features that have been achieved in YAG coatings, including:
- High porosity to maximize insulation performance
- Low porosity to increase toughness and erosion resistance
- Vertical through-thickness cracks to relieve strain and inhibit fracture
- Transverse bands of low porosity (“inter-pass boundaries,” or IPBs) to reduce thermal conductivity
Leveraging these capabilities, the project team is developing novel coating microstructures that tailor and optimize performance for specific applications. Two components were selected for this optimization: a combustion liner and a turbine-blade outer air seal (tipshoe).
Gas-Turbine Combustion Liner
Application requirements for the combustion liner (Fig. 3) include a low thermal conductivity overall, strong resistance to erosion at the outer surface and strain tolerance near the metallic bondcoat to accommodate thermal-expansion mismatch. Given these requirements, a graded-porosity strategy was deployed (Fig. 4).
YAG with a high density was applied near the metallic bondcoat (to improve strain tolerance). The coating then transitioned into a porous region with IPBs (to minimize overall thermal conductivity). Finally, the outermost region transitioned back to a high density (to improve erosion resistance at the surface). Through-thickness cracking was also incorporated to provide strain tolerance.
Following validation of coating performance in laboratory testing, a full-size combustion liner was coated with YAG in the optimized microstructure. This application was the first large-scale component coated with this technology. Compared to the fuel-nozzle application, temperature control and application distance were significant challenges for this larger and more complex part. The YAG coating will be compared against the standard YSZ coating in an upcoming rig test and ultimately deployed in development engine testing.
Turbine Blade Outer Air Seal (Tipshoe)
YAG development has also been initiated for blade outer air-seal applications (Fig. 5). This application requires a porous outer layer for possible interaction with the rotating turbine blade; yet it must also be durable against erosion, corrosion and thermal stresses. Process and coating development are in progress to fabricate coatings for “rub-rig” testing that will simulate the application conditions.
Conclusion and Next Steps
With significantly higher-temperature phase stability than state-of-the-art YSZ, the emerging YAG system is a promising candidate as a next-generation TBC. Solar Turbines Inc. (in partnership with Solution Spray Technologies) is now scaling up the novel SPPS deposition technique to validate the performance of a YAG coating on gas-turbine components in both rig and engine testing.
The next step in the program will be to validate the performance of the optimized YAG coating on a full-scale combustion liner in a rig test. Successful demonstration will lead to a development engine test of a coated combustion liner. Process development will also continue for blade outer air-seal applications.
The highlighted project is an example of work funded under AMO’s technical focus area of Materials for Harsh Service Conditions. To learn more about AMO’s research portfolio in this and other technical areas, visit AMO’s website at https://energy.gov/eere/amo/advanced-manufacturing-office.
- M. Gell, et al., “Higher temperature thermal barrier coatings with the combined use of yttrium aluminum garnet and the solution precursor plasma spray process,” Journal of Thermal Spray Technology, 27 (2018) 543-555
- N. P. Padture and P. G. Klemens, “Low thermal conductivity in garnets,” Journal of the American Ceramic Society, 80 (1997) 1018-1020
- R. Vassen, A. Stuke, and D. Stöver, “Recent developments in the field of thermal barrier coatings,” Journal of Thermal Spray Technology, 2009 (18) 181-186
- M. P. Schmitt, et al., “Durable aluminate toughened zirconate composite thermal barrier coating (TBC) materials for high temperature operation,” Journal of the American Ceramic Society, 102 (2019) 4781-4793
- A. D. Jadhav, et al., “Low-thermal-conductivity plasma-sprayed thermal barrier coatings with engineered microstructures,” Acta Materialia, 54 (2006) 3343-3349
All images/graphics have been provided by the author.