Airfoil trailing-edge cooling is the main focus. Test rig, made up of two adjacent channels, simulated trailing-edge and mid-chord cavities of an airfoil. Eleven holes, drilled on partition wall between the two channels produced eleven crossover jets that impinged on the rib-roughened wall. The jets, after impinging on their respective target surface, turned towards the trailing-edge channel exit. Baseline smooth target wall as well as four rib angles with flow of 0, 45, 90 and 135 degrees are investigated. Crossover holes axes were on trailing-edge channel center plane i.e. no tilting of cross-over jets. Steady state liquid crystal thermography technique was used in this study for a range of jet Reynolds number of 10000 to 35000. Test results are compared with numerical results obtained from the Reynolds-averaged NavierStokes and energy equation. Closure was attained by k-w with Shear Stress Transport model. The numerical work was performed for boundary conditions identical to those of the tests. In addition to the impingement heat transfer coefficients, numerical results provided the mass flow rates through individual cross-over holes. This study concluded that: a) local Nusselt numbers correlate well with local jet Reynolds numbers, b) 90o ribs, that is when the cross-over jet axis was parallel to rib longitudinal axis, produced higher heat transfer coefficients, compared to other rib angles, and c) Numerical heat transfer results were generally in good agreement with test results. The overall difference between the two was about 10%


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    Titel :

    CROSSOVER JET IMPINGEMENT IN A RIB-ROUGHENED TRAILING-EDGE COOLING CHANNEL


    Beteiligte:


    Erscheinungsdatum :

    2016




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    52.30 / 52.30 Strömungskraftmaschinen, Turbomaschinen