Abstract
†‡ ‡ ‡ ‡ An active flow control concept has been advanced in this paper to minimize the intensity and size of secondary flow in gas turbine. Using the numerical simulation method that has been validated with experimental data, this paper explore the feasibility of the suppressing of the secondary flow in turbine blade passage corner with small-jets, a well known active flow control method. The results show that the jets exhausting through small slot in the blade surface on end-wall region could suppress the corner separation, this suppressing is effective to reduce the secondary flow loss. It is shown that, because of the suppressing of the secondary flow separation, the total pressure loss of the turbine blade passage flow was significantly reduced. The jet located on the leading edge with a chord-wise configuration is effective, and the jet with only 0.006% of the blade passage flow mass could reduce the 30% of the total pressure loss of turbine blade.
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