Abstract
Jet into crossflow has numerous technological applications, such as in film cooling of gas turbine blades. It has been more than half a century that people have been studying this problem and research is still underway due to its importance and its complexities. This paper is a computational study concerned with film cooling of gas turbine blades. A novel near-wall flow control technique of using staggered arrangement of small injection ports near a film-cooling hole (combined triple jet) is introduced. The fluid injected from the small ports changes the flow pattern downstream, resulting in a considerable enhancement of cooling efficiency. The flowfield computations, governed by the Reynolds-averaged Navier-Stokes equations (incorporating the Reynolds stress turbulence model), were performed using the SIMPLE algorithm on a nonuniform staggered grid. The results show that, due to the introduction of new counter-rotating vortex pairs, this approach provides considerable improvement in 1) film-cooling efficiency, 2) uniform distribution of the coolant film, 3) reduction of the mixing strength between the freestream and the coolant jets, and 4) reduction of skin friction drag. In addition, qualitative comparison of our results with those of regular staggered holes arrangement indicated that this new technique has a considerably higher film-cooling performance.
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