Abstract Ceramic Matrix Composites (CMCs) are primary candidates for advanced gas turbine engine application that require intense high temperature tests and validations. Before CMCs used in engine hot sections, a lot of tests need to be done, especially thermal test. A thermal test rig has been set up to simulate the engine turbine thermal environment. Propane gas is used to simulate the practical aviation fuel and compressed air with flow regulator is used as cooling media. The capabilities and limitations of the test facility have been calibrated and discussed in this paper. A CMC turbine vane with internal cooling path was tested on this burning rig. The results showed that the CMC vane could withstand the 1200 ℃ thermal cycling test but the coating was disappeared. It has been proved that such test rig and method could simulate the thermal boundary conditions of turbine vanes and blades.

中文翻译：

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陶瓷基复合材料涡轮叶片热模拟试验与评价

摘要 陶瓷基复合材料 (CMC) 是先进燃气涡轮发动机应用的主要候选材料，这些应用需要强烈的高温测试和验证。在发动机热工段使用CMC之前，需要进行大量的试验，尤其是热试验。已经建立了一个热试验台来模拟发动机涡轮热环境。丙烷气用于模拟实际航空燃料，并使用带流量调节器的压缩空气作为冷却介质。测试设施的能力和局限性已在本文中进行了校准和讨论。带有内部冷却路径的 CMC 涡轮叶片在该燃烧设备上进行了测试。结果表明，CMC叶片能经受1200℃热循环试验，但涂层消失。