| Budget Amount *help |
¥4,810,000 (Direct Cost: ¥3,700,000、Indirect Cost: ¥1,110,000)
Fiscal Year 2019: ¥1,430,000 (Direct Cost: ¥1,100,000、Indirect Cost: ¥330,000)
Fiscal Year 2018: ¥1,430,000 (Direct Cost: ¥1,100,000、Indirect Cost: ¥330,000)
Fiscal Year 2017: ¥1,950,000 (Direct Cost: ¥1,500,000、Indirect Cost: ¥450,000)
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| Outline of Final Research Achievements |
Cooling at trailing edge of gas turbine airfoil is one of the most difficult problems because of its thin shape: high thermal load from both surfaces, hard-to-cool geometry of narrow passages, and at the same time demand for structural strength are the reasons. The objective of this study is to further improve the trailing-edge film cooling performance by using cooling-flow pulsation. Heat transfer coefficient and film cooling effectiveness on cutback surface were measured by a transient infrared thermography technique with consideration of three-dimensional heat conduction. The flow field was measured by a stereo PTV method. Furthermore, numerical analyses were performed by LES and DNS methods. The measurements and computations were performed by varying the pulsation parameters and the cutback-surface geometries. From the results, optimum values were identified and the principle of the thermal shield and convective cooling by the cooling-flow pulsation was explained.
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