A segment of transpiring wall is installed near a row of unshaped film holes. The effects on the aerodynamic performance and cooling downstream of the row of cylindrical holes in the presence of transpiration is studied numerically. The changes in behavior of the film due to relative positioning of the injection sources and blowing ratios are predicted to understand the sensitivity of cooling and aerodynamic losses on the relative positioning of the two sources and each blowing ratio. The results indicate that a coupling of the two sources allows a more efficient use of coolant by generating a more uniform initial film resulting in improved component durability through reduction of hot- streaks. With careful optimization the discrete holes can be placed farther apart laterally operating at a lower blowing ratio with a transpiration segment making the large deficits in cooling effectiveness mid-pitch less severe, overall minimizing coolant usage. Addition of transpiration increases the aerodynamic losses associated with injection. This effect can be arguably small compared to corresponding thermal benefits seen by coupling the two. Comparisons of linear superposition predictions of the two independent sources with the corresponding coupled scenario indicate the two films positively influence one another and outperform predictions. The interaction between the two films is dependent upon the relative placement of the transpiration; all relative placements have an overall beneficial effect on the cooling seen by the protected wall. An increase in area-averaged film cooling effectiveness of 300% is seen along with only a 50% increase in loss coefficient by injecting an additional 10% coolant. In this study the downstream placement of transpiration is found to perform best of the three geometries tested while considering cooling, aerodynamic losses, local uniformity and manufacturing feasibility. With further study and optimization this technique can potentially provide more effective thermal protection at a lower cost of aerodynamic losses and spent coolant. A method of measuring the local temperature of a porous wall is also discussed. Measurements are taken with temperature sensitive paint applied in thin coats to the wall. This technique was validated on a 40PPI, 7% relative density aluminum porous coupon. Measurements of discharge coefficients as well as downstream effectiveness data are included to verify the flow through the porous wall was unaltered by applying the paint. A maximum deviation in film-cooling effectiveness of 9% between the two cases with the majority of data falling within 4% was found, very similar to the experimental uncertainty of the rig. This excellent agreement between the repeated tests showed that by applying thermal paint to a wall of such porosity does not significantly affect the flow exiting the wall and hence the measurement technique can readily be applied to transpiration cooling studies at this scale. Methods of filtering the temperature sensitive paint on the porous wall are presented.

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Full-coverage film cooling is investigated both experimentally and numerically. First, surface measurements local of adiabatic film cooling effectiveness and heat transfer augmentation for four different arrays are described. Reported next is a comparison between two very common turbulence models, Realizable k-ε and SST k-ω, and their ability to predict local film cooling effectiveness throughout a full-coverage array. The objective of the experimental study is the quantification of local heat transfer augmentation and adiabatic film cooling effectiveness for four surfaces cooled by large, both in hole count and in non-dimensional spacing, arrays of film cooling holes. The four arrays are of two different hole-to-hole spacings (P/D = X/D = 14.5, 19.8) and two different hole inclination angles (α = 30◦ , 45◦ ), with cylindrical holes compounded relative to the flow (β = 45◦ ) and arranged in a staggered configuration. Arrays of up to 30 rows are tested so that the superposition effect of the coolant film can be studied. In addition, shortened arrays of up to 20 rows of coolant holes are also tested so that the decay of the coolant film following injection can be studied. Levels of laterally averaged effectiveness reach values as high as ¯η = 0.5, and are not yet at the asymptotic limit even after 20 − 30 rows of injection for all cases studied. Levels of heat transfer augmentation asymptotically approach values of h/h0 ≈ 1.35 rather quickly, iii only after 10 rows. It is conjectured that the heat transfer augmentation levels off very quickly due to the boundary layer reaching an equilibrium in which the perturbation from additional film rows has reached a balance with the damping effect resulting from viscosity. The levels of laterally averaged adiabatic film cooling effectiveness far exceeding ¯η = 0.5 are much higher than expected. The heat transfer augmentation levels off quickly as opposed to the film effectiveness which continues to rise (although asymptotically) at large row numbers. This ensures that an increased row count represents coolant well spent. The numerical predictions are carried out in order to test the ability of the two most common turbulence models to properly predict full coverage film cooling. The two models chosen, Realizable k − ε (RKE) and Shear Stress T ransport k − ω (SSTKW), are both two-equation models coupled with Reynolds Averaged governing equations which make several gross physical assumptions and require several empirical values. Hence, the models are not expected to provide perfect results. However, very good average values are seen to be obtained through these simple models. Using RKE in order to model full-coverage film cooling will yield results with 30% less error than selecting SSTKW.

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