ヒートパイプを利用したタービン冷却システムの研究 : 高温化ヒートパイプ性能とシステム成立性評価(熱工学,内燃機関,動力など)

Alternative turbine cooling schemes should be applied for future aero-engine to increase turbine inlet temperature. To estimate feasibility of this new cooling system, several experiments were conducted with some kind of heat pipes. Although sodium heat pipe with sintered powder metal wick assisted argon gas showed good performance, the highest heat flux on the evaporator was insufficient because of the temperature limit of the heat pipe shell material. To increase heat transport, heat pipe length is reduced and heat pipe shell is changed into heat resistance material. In the result, large amount of heat transport were demonstrated, with 38 W/cm2 as the heat flux, however start-up time was increased slightly. Since the results show a 46% decrease in cooling air and a 5.4% increase in specific thrust with this heat pipe as the turbine cooling system, this advanced cooling system is practical to apply.