Development of 1400°C(2552°F) class Ceramic Matrix Composite Turbine Shroud and Demonstration Test with JAXA F7 Aircraft Engine

Fumiaki Watanabe, Shohei Yamanaka, Toshihito Noguchi, Hiroto Hirano, Hayao Sato, M. Makida, Masahiro Hojo
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Abstract

The Authors developed 1400°C(2552°F) class CMC material system which consist of SiC fibers and SiC matrix and ytterbium silicate base matrix, aiming for higher temperature capability. Then they designed and manufactured high pressure turbine shrouds for aircraft engines using that 1400°C class material system, and they conducted strength tests and thermal cycle tests for turbine shroud components. After that they conducted engine tests for the CMC turbine shrouds demonstration in the actual engine environment jointly with the Japan Aerospace Exploration Agency (JAXA) in 2021. The engine test was conducted for over 75 hours including over 35 hour hot time. After the test teardown inspection was conducted. No spallation of EBC, no recession and no wear on CMC turbine shrouds were found. As the result of the microstructure observation for cut faces of CMC turbine shrouds, no oxidation in SiC fibers, no chemical reaction in matrix, and no microcrack in matrix were found, but, some oxidation in fiber interface coating and microcrack in EBC were found. Bending strength tests with specimens cut out from CMC turbine shrouds were conducted in order to survey the degradation of material. As the result of bending test, the strength of the specimens cut out from engine tested shrouds were equivalent to the strength of the specimens cut out from unused shrouds. The CMC turbine shrouds after engine test were determined to be serviceable, therefore the developed 1400°C class CMC shrouds was proven to be sound in an actual engine environment.
1400°C(2552°F) 级陶瓷基复合材料涡轮护罩的开发及在 JAXA F7 飞机发动机上的演示试验
作者开发了 1400°C(2552°F)级 CMC 材料系统,该系统由碳化硅纤维、碳化硅基体和硅酸镱基体组成,旨在实现更高的耐温能力。然后,他们使用这种 1400°C 级材料系统设计并制造了飞机发动机的高压涡轮护罩,并对涡轮护罩部件进行了强度测试和热循环测试。之后,他们于 2021 年与日本宇宙航空研究开发机构(JAXA)联合进行了 CMC 涡轮护罩在实际发动机环境中的发动机试验。发动机试验进行了超过 75 小时,其中包括超过 35 小时的热时间。试验结束后进行了拆卸检查。没有发现 EBC 的剥落,也没有发现 CMC 涡轮护罩的衰退和磨损。对 CMC 涡轮护罩切割面的微观结构观察结果表明,SiC 纤维未发生氧化,基体未发生化学反应,基体未出现微裂纹,但纤维界面涂层出现了一些氧化,EBC 出现了微裂纹。为了检测材料的降解情况,对从 CMC 涡轮护罩上切割下来的试样进行了弯曲强度测试。弯曲试验结果表明,从发动机试验过的护罩上切割下来的试样强度与未使用过的护罩上切割下来的试样强度相当。发动机测试后的 CMC 涡轮护罩确定可以使用,因此开发的 1400°C 级 CMC 护罩在实际发动机环境中证明是可靠的。
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