The invention discloses a zero cooling turbine blade of aeroengine consumption intensity of super cooling device, relates to the technology of turbine blade cooling, the turbine blade, blade from leading to trailing edge processing a plurality of horizontal hole channel, will end adjacent channel hole connected to a channel, with two pipe of turbine blade trailing edge near the end hole are respectively communicated with the radiator import and export, to form a closed connected internal cooling passage, including cooling channel filled with high pressure liquid. When the high temperature gas turbine blade feel when in high temperature gas heat driven, high pressure liquid cooling channel formed in the inner loop, the circulating flow of heat from the radiator away, so as to realize the super strength of cooling turbine blade without cooling air condition. The invention can improve the efficiency of turbine blade cooling without cooling air, increasing turbine inlet temperature, thereby improving the aero engine thrust weight ratio, reduce the manufacturing cost of aero engine.
【技术实现步骤摘要】
【技术保护点】
１．一种航空发动机涡轮叶片的零冷气消耗超强度冷却装置，其特征是：在涡轮叶片内部，自叶片前缘到尾缘横向加工多条圆孔通道，将相邻圆孔通道的首尾相互连通成一条通道，用两根导管将涡轮叶片前后缘附近的首尾圆孔分别与散热器进出口相连通，构成密闭的连通内冷通道，在内冷通道内充满高压液体；当涡轮叶片感受到高温燃气时，在高温燃气的热驱动下，内冷通道内的高压液体形成内循环，其循环流动中的热量由散热器带走，从而在无需冷却气的情况下实现对涡轮叶片的冷却。
【技术特征摘要】
【专利技术属性】
技术研发人员：朱俊强，唐大伟，卢新根，徐纲，李玉华，袁达忠，
申请(专利权)人：中国科学院工程热物理研究所，
类型：发明
国别省市：11[中国|北京]
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