experimental investigation of impingement heat transfer in a rib-roughened trailing-edge channel with crossover holes
A modern day turbine blade for a typical gas turbine usually contains rib roughened cavities which increases the cooling rate. There are several methods of cooling which include the impingement cooling method, the film cooling method, and the rib roughened cooling method. The trailing edge cooling c...
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| Online Access: | http://hdl.handle.net/2047/d20000328 |