|关键词: 航空发动机 涡轮导向叶片 前缘冷却 陶瓷基复合材料 数值仿真
|Thermal protection of turbine guide vane with ceramic matrix composite armor
SUN Zhiqiang, LYU Dong, ZHU Kaidi, LIU Yingshi, KONG Xingao
Innovation Lab of Gas Turbine Blade，School of Energy and Power Engineering，Dalian University of Technology， Dalian 116024，China
|To improve the thrust-to-weight ratio of aero-engines， it is crucial to overcome the current limitations of superalloy and film cooling on the temperature capacity of turbine blades， as well as the challenges associated with the difficulty of ceramic matrix composite （CMC） turbine blade manufacturing. Therefore， novel scheme was proposed in this paper， which installed CMC armors as vane leading edge thermal protection. And numerical simulations with wide operating conditions were applied to study the differences in flow and heat transfer compared with the typical film cooling scheme. At the same pressure ratio of 1.03， the coolant mass flow rate can be greatly reduced by 58% due to the combined effect with the CMC armors. On the other hand， the cooling efficiency also increased from 0.50 to 0.85 significantly， which showed the great effect of CMC armor protection. The temperature margin of CMC armor erosion failure was studied forward by variation of its thermal conductivity. The conservative result of the allowable gas temperature was 2017K， which could meet the requirements of the 5th-generation aero-engines through further performance optimizations of CMC materials and armor schemes.
|Key words: Aero-engine Turbine guide vane Leading edge cooling Ceramic matrix composites Numerical simulation