摘要
为保障涡轮叶片正常工作,面对不断提高的涡轮前温度,发展更高效的冷却技术显得尤为迫切。陶瓷基复合材料(ceramic matrix composite,CMC)发汗冷却技术结合了CMC优异的高温耐受性与发汗冷却的高效散热潜力,在未来的涡轮叶片热防护中具有广阔的应用前景。然而,CMC材料强烈的各向异性及其内部复杂的多孔结构,为其发汗冷却过程的热分析带来很大挑战,相关流动与传热机制也不明确。对CMC各向异性导热系数和微孔隙渗流特性方面的研究进展进行了综述,分析了当前研究存在的关键问题与难点,并为建立面向CMC涡轮叶片发汗冷却结构的整体设计体系提出了建议。
To ensure the normal operation of turbine blades Facing continuously increasing turbine inlet temperatures,the development of more efficient cooling technologies has become particularly urgent.Ceramic matrix composite(CMC)transpiration cooling technology combines the excellent high-temperature resistance of CMC with the efficient heat dissipation potential of transpiration cooling,showing broad application prospects in future thermal protection of turbine blades.However,the strong anisotropy of CMC materials and their complex internal porous structure pose significant challenges for the thermal analysis of the transpiration cooling process,and the underlying flow and heat transfer mechanisms remain unclear.This review summarized recent research progress on the anisotropic thermal conductivity and microporous seepage characteristics of CMC,analyzed key existing problems and challenges in current studies,and offerd suggestions for establishing a comprehensive design framework for CMC turbine blade transpiration cooling structures.
作者
李广超
乔楚涵
赵志奇
洪潮
赵长宇
LI Guangchao;QIAO Chuhan;ZHAO Zhiqi;HONG Chao;ZHAO Changyu(College of Aero-engine,Shenyang Aerospace University,Shenyang 110136,China)
出处
《沈阳航空航天大学学报》
2025年第6期1-11,共11页
Journal of Shenyang Aerospace University
基金
国家自然科学基金(项目编号:52376028)。
关键词
陶瓷基复合材料
发汗冷却
各向异性导热系数
微孔隙渗流
CMC涡轮叶片
ceramic matrix composite
transpiration cooling
anisotropic thermal conductivity
microporous seepage
CMC turbine blade
