Numerical Study on Cooling Performances of Short Fan-shaped Film Holes on a Double-wall Cooled Turbine Vane
To capture the cooling mechanisms of fan-shaped film-holes at the surface of advanced doble-wall cooled vanes,a conjugate heat transfer numerical simulation was conducted to examine the cooling characteristics of typical 7-7-7 and 1 1-11-11 fan-shaped film cooling holes on the double-wall turbine vane.Under a large range of blowing ratios from 0.6 to 2.4,three distinct fan-shaped film hole arrangements were compared,including:1)SH1 layout where both the suction and pressure sides were equipped with 7-7-7 fan-shaped holes;2)SH2 layout where both sides featured 11-11-11 fan-shaped holes;and 3)proposed SH3 layout where the suction side was equipped with 7-7-7 holes while the pressure side had 11-11-11 holes.In addition,the cylindrical-hole was chosen as the reference.The comparisons of numerical results revealed that relative to the cylindrical-hole layout,the designs of fan-shaped-hole can improve the overall effectiveness by 17％at suction side and 7％at pressure side at least,respectively.However,the designs of fan-shaped-hole can induce the larger thermal gradient over two sides of vane.Application of SH3 can displayed the smallest discrepancy in cooling effectiveness between the suction and pressure sides among three types of fan-shaped-hole-configurations,due to the more proper outflow allocation.The benefit of SH3 can be enlarged under the larger blowing ratio.In comparison with the cooling at suction side,the cooling effectiveness at pressure side is more sensitive to the configuration of film-hole,bringing to the larger challenge for the cooling optimization.
Double-wall Cooled VaneShort Fan-shaped HoleFilm CoolingIsomeric LayoutFluid-soid Coupled Heat Transfer
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