Double Shell Type Turbine Vane Cooling Design And Research

In order to increase the thrust to weight ratio in the modern aero engines, the turbine inlet temperature will be further increased. Today, the turbine inlet temperature reaches 1800K～2000K for the series of aero engines whose thrust to weight ratio reaches 10, and further high turbine inlet temperature reaches 2100K～2300K (thrust to weight ratio 15～20). The hot gas temperature far exceeds the material permissible temperature of high temperature alloy. The multiple high efficiency cooled turbine vane merely fill the demand of the aero engine whose thrust to weight ratio reaches 10. In order to develop next generation higher performance aero engine, we have to develop new high efficiency cooling techniques of turbine vane.In this paper, the new type double wall high efficiency cooled turbine vane was designed using the foreign advanced cooling techniques of turbine vane and the thought way of high technology origin and large technology span for reference, and the experimental study was carried out to investigate the cooling techniques on the turbine vane syntheses cooling performance experimental facility. The cooling techniques of film shower-cooling, film spill internal heat transfer coefficient enhancement and new type double-wall narrowness space impingement-film cooling were used in the turbine vane. The goal of investigation is to develop a high efficiency cooled turbine vane for next generation higher performance aero engine whose thrust to weight ratio reaches 15～20.The test results show that the average absolute cooling performance and relative cooling performance reach 977℃and 0.75 at the mid-section, and the cooling performance fulfills the design goal. The cooling techniques of turbine vane are close to the foreign advanced aero engine turbine vane cooling level (thrust to weight ratio reaches 15～20).