The research focuses on testing the film cooling effectiveness on a gas turbine
blade suction side surface. The test is performed on a five bladed cascade with a
blow down facility. Four different blowing ratios are used in this study, which are
0.5, 1.0, 1.6, and 2.0; mainstream flow conditions are maintained at exit Mach
number of 0.7, 1.1 and 1.3. Nitrogen is injected as the coolant so that the oxygen
concentration levels can be obtained for the test surface. Based on mass transfer
analogy, film cooling effectiveness can be computed with pressure sensitive paint
(PSP) technique. The effect of blowing ratio on film cooling effectiveness is
presented for each testing condition. The spanwise averaged effectiveness for
each case is also presented to compare the blowing ratio and mainstream effect on
film cooling effectiveness. Results show that due to effects of shock, the optimum
blowing ratio is 1.6 for exit Mach number of 1.1 and 1.3; however; without the
effects of shock, the optimum blowing ratio is 1.0 for exit Mach number of 0.7.
| Identifer | oai:union.ndltd.org:tamu.edu/oai:repository.tamu.edu:1969.1/ETD-TAMU-2009-08-2927 |
| Date | 14 January 2010 |
| Creators | Liu, Kuo-Chun |
| Contributors | Han, Je-Chin |
| Source Sets | Texas A and M University |
| Language | en_US |
| Detected Language | English |
| Type | Book, Thesis, Electronic Thesis |
| Format | application/pdf |
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