CMC Material Analysis Under Deflagration Conditions of Hydrogen Combustion

Carbon based fuels have been the main energy source for power generation systems and propulsion applications. To reduce emissions, there has been a growing interest in hydrogen as a cleaner and more sustainable energy source. While renewable hydrogen production and efficient storage systems are essential components of this transition, the development of advanced materials that can endure the harsh conditions of hydrogen combustion is particularly crucial. Traditionally, the hot sections of gas turbine engines have relied on superalloys with thermal barrier coatings; however, the significant higher flame temperatures associated with hydrogen combustion demands the development of a new type of materials capable of withstanding these extreme operating conditions. Amongst the emerging alternatives, Ceramic matrix composites materials have been studied for the past several years and they are considered a suitable candidate to replace the superalloys with TBC´s. This study evaluates the thermal performance of a CMC material under deflagration conditions within a hydrogen combustor. The combustor operates at various conditions, but for this experiment, it was set to an equivalence ratio of 0.44, a temperature of 1232 °C and a pressure of 4.4 bar. The material is directly exposed to the hot combustion gases to analyze its ability to withstand and insulate the high temperatures produced in the thermal environment. Preliminary results of the CMC material show promising thermal resistance; however further testing needs to be performed to fully validate its long-term durability and performance.