Abstract:

Heat transfer coefficients downstream of film row at different locations on turbine blade surface were studied experimentally. A threeblade liner cascade in a large-scale low-speed opening wind tunnel was used in the experiment. There were 6 rows of film cooling holes at the middle blade and one row on the suction surface, three rows on the leading edge and wto rows on the pressure surface. Heat transfer coefficients on the blade surface were measured at different blowing ratios and density ratios and the same Reynolds number.

Key words: turbine , blade,  , film , cooling,  , density , ratio,  , heat , transfer , coefficient