Abstract:

According to front-line feedback, turbine blade erosion is increasing, bringing huge pressure to the maintenance and operation of airlines. The root cause of blade ablation is that the traditional cooling structure cannot meet the needs of gas temperature rise. A new type of slit cooling structure is proposed and its structure cooling effect is verified through numerical calculation on both cooling efficiency and pneumatic loss. Results show that in appropriate range of blowing ratio, the seam type structure makes obvious uniform cooling effect in both spanwise and extending direction of blade. It significantly reduces thermal stress generated by uneven cooling on blade surface, so the extent of blade ablation is reduced and the service life of blade is extended. Simultaneously the seam structure is also superior to traditional structure in the pressure loss, cleaning and maintenance.

Key words: film cooling, blade, even cooling, pressure loss