Title

Measurements and modeling of transpiration cooling

Abstract

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.

Notes

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Thesis Completion

2010

Degree

Bachelor of Science (B.S.)

College

College of Engineering and Computer Science

Degree Program

Aerospace Engineering

Subjects

Dissertations, Academic -- Engineering and Computer Science;Engineering and Computer Science -- Dissertations, Academic

Format

Print

Identifier

DP0022558

Language

English

Access Status

Open Access

Length of Campus-only Access

None

Document Type

Honors in the Major Thesis

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