Experimental investigation of heat transfer for rotating internal cooling channels with rib turbulators

To deeply understand the heat transfer distribution in rotating ribbed serpentine cooling channel with high pressure turbine blade, the internal cooling channel experimental system has been set up. The heat transfer theory in cooling channel of rotor blade was researched by using transient liquid crystal measurement. The heat transfer results between experimental date and numerical simulation were compared. The range of Reynold numbers on channel inlet and Rotation numbers are from 5000 to 17000, 0.0 to 0.09, respectively. The hydraulic diameter divided by radius of gyration is 46.4. The results show that local heat transfer distribution in serpentine channel is similar to different Reynold numbers. The local and average heat transfer coefficient increases with the augment of the Reynold number. The spanwise of averaged heat transfer coefficient distributes in multiple-peak form along the flow direction. The heat transfer enhancement by rib turbulators decreases along the flow direction. The radial outflow Nusselt number (Nu) increases and the radial inflow Nu decreases in trailing surface with the augment of the rotation number. The local heat transfer coefficient in downstream of turning area is changed by Coriolis force. The high heat transfer area of intercostal is shifted from downstream of the first rib to the middle of two ribs.