摘要：开展航空发动机的预研工作，是推动航空事业发展的重中之重，未来航空发动机涡轮前温度将达到2400K以上，针对发动机重要部件涡轮导叶的热防护问题，需要提出新型冷却方案。结合高温热管导热能力强、均温性好等优势，本文提出了一套热管涡轮导叶的初步设计方案。结合热管传热极限的计算方法，分析了结构和工作温度对高温热管性能的影响，为热管涡轮导叶设计提供理论依据。
Abstract:Conducting preliminary research on aero-engines is crucial for advancing the aviation industry. The anticipated pre-turbine temperatures of future aero-engines will exceed 2400 K. Addressing the thermal protection of turbine vanes, integral to engine performance, requires the introduction of a novel cooling approach. This study proposes a preliminary design scheme for heat pipe turbine vane, leveraging the high thermal conductivity and uniform temperature distribution characteristic of high temperature heat pipes. The analysis incorporates heat transfer limitations calculations for heat pipes, assessing how structural design and operational temperatures influence their performance. These insights aim to establish a theoretical framework for the design of heat pipe turbine vane.

 

热管涡轮导叶,热防护,设计计算,传热极限