论文部分内容阅读
高性能飞行器的发展必须有先进发动机与之匹配,现代的航空/航天发动机不仅推力大,而且推重比不断提高。随着发动机推力和效率的提高,发动机的涡轮进口温度需不断提高。未来的航空发动机要求其热端关键部件在1100℃以上的高温和复杂载荷条件下长期可靠使用,因此传统的镍基和钴基高温合金已经不能满足下一代高性能先进发动机的需求。超高音速飞行器与空气的剧烈摩擦产生的热量,会导致鼻锥、机翼前缘、机翼挡板等的温度升高到2000℃左右。密度低、抗烧蚀、导热好、抗热冲击和热震性良好的碳/碳复合材料是最佳的选择,但碳/碳复合材料的主要问题是高温环境下的氧化。
The development of high-performance aircraft must have advanced engines to match, modern aerospace / aerospace engines not only thrust large, and the thrust-weight ratio continues to increase. As engine thrust and efficiency increase, the engine’s turbine inlet temperature needs to continue to increase. Future aircraft engines require long-term reliable use of their hot-key components at temperatures above 1100 ° C and complex loads, so that traditional nickel and cobalt-based superalloys are no longer sufficient for the next generation of high-performance advanced engines. The heat generated by the intense friction between the ultra-high-speed vehicle and the air causes the temperature of the nose cone, wing leading edge, wing baffle, etc. to rise to about 2000 ° C. Low density, good resistance to ablation, good thermal conductivity, good thermal shock resistance and thermal shock resistance of the carbon / carbon composite material is the best choice, but the main problem of carbon / carbon composites is high temperature oxidation.