214 革新的タービン翼冷却構造に関する研究 : 感温液晶による熱伝達特性計測(流体工学)

抄録

An advanced cooling system for turbine blades is a key factor to realize supersonic transport propulsion system and utilize it practically. This study deals with heat transfer measurements inside of a cooling configuration designed for ultrahigh temperature turbine blades. The cooling configuration concerned integrates impingement cooling and pin-fin cooling devices into one body. A large scaled model employed in this study is constructed from acrylic resin materials to measure the heat transfer on the surfaces of the film cooling plate and pin-fins. The measurements are executed by a transient technique using thermochromics liquid crystal (TLC). This technique makes it possible to grasp quantitative information of the heat transfer distribution over the surfaces. A focus is on the effect of the pin height upon the local and averaged heat transfer characteristics.