Abstract
The paper is concerned with flow past compressor blade cascade (NACA 65 with thickened trailing edge) at off-design regimes, which are characteristic by partial or complete flow separation on the suction surface of the blades. An attempt has been made to moderate the flow separation using continuous or periodic blowing from the sidewalls. The flow field was visualized using schlieren technique and surface paint visualization. The visualizations were complemented by measurement of the static pressure distribution on the suction surface of the blades. In agreement with the literature, the visualizations confirmed a complexity of the 3-dimensional flow separation, which was intensified by influence of the sidewall boundary layers developing from upstream parts of the test section. Furthermore, it was found out that the effect of both continuous and periodic blowing was rather minor. Finally, the results agree with the available literature showing that it is highly difficult to considerably control the complex 3-dimensional flow separation in the compressor cascade by control jets issuing (only) from the sidewalls
Highlights
Flow through compressor blade cascades, under higher loading at higher angle of attack, tends to separate
In agreement with the literature, the visualizations confirmed a complexity of the 3-dimensional flow separation, which was intensified by influence of the sidewall boundary layers developing from upstream parts of the test section
The results agree with the available literature showing that it is highly difficult to considerably control the complex 3-dimensional flow separation in the compressor cascade by control jets issuing from the sidewalls
Summary
Flow through compressor blade cascades, under higher loading at higher angle of attack, tends to separate. A very promising strategy consists in an implementation of flow oscillation. Various locations of the actuation were suggested by Culley et al [1]. Well feasible design uses an actuation from channel sidewalls, as was investigated with the two-dimensional blade cascades, e.g. by Matějka et al [2] and, more recently, by Zander et al [3]. A very efficient location was found at the suction side of the blade, at a vicinity of the flow separation, namely at 14.5% of the suction side length from the leading edge – Zander et al [3]. The present investigation uses approximately the same location, as is describe below
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