<p>There is a continuous growth in different sectors of engineering and technology resulting in a high demand of modern and innovative application into providing solutions to all barriers. With the increase in modern age demand technology is growing rapidly, hence the requirement of modern system. Power required to reach at such high speed, gas turbine propulsion system is responsible to provide thrust and power to its other component. In modern gas turbine application, high power and thermal efficiency are in high demand and are essential requirement. There are two important parameters in increasing thermal efficiency of gas turbine are its compression ratio and higher hot gas inlet temperature and this gas turbine are based on Brayton cycle. This advanced gas turbine has inlet temperature, which exceed the material thermal limitation, which are used for blade. This high temperature has an impact on the strength and life of blade employed for working. The current study produces analysis in methods dealing with increasing the cooling effectiveness of the turbine blade which are working under very high temperature hot gases exit from the combustion chamber. This gas expands into the turbine region by which thrust and/or power is developed. This high temperature gases can have a considerable effect on the working life and stresses are produced into turbine blade. This turbine blade can lead to failure under cyclic loading of this hot gases. This</p><p>has to be taken into consideration and a proper cooling system has to be employed.&nbsp; Cooling effectiveness can also lead the system which has a working temperature range of 800K can also work under 1000K inlet temperature with its improved cooling system. We present a method of improving the internal cooling for turbine blade with the help of latest improved material such as thermal barrier coating (TBC) and environmental barrier coating (EBC). The study focusses on effect of this TBC, EBC and combination of TBC-EBC layer employed on to the surface of blade. Analysis of result obtained from this conjugate heat transfer (CHT) studies have shown good agreement with the experimental data. Comparison revealed use of SST k-omega model was efficient and predicted with similar trend as of the experimental for pressure were as with 3% of deviation and for temperature, it over and under estimate over some region. This deviation was well under 3-5%.</p>

Comparative Study of Barrier Coatings on Turbine Blade Cooling

Paper Proceedings: https://asmedigitalcollection.asme.org/GTINDIA/GTINDIA2021/volume/85536

ASME 2021 Gas Turbine India Conference (GTINDIA2021)

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