Flow and Temperature Measurements in a Linear Turbine Blade Passage with Leading Edge and Endwall Contouring and with and without Film Cooling
Gas turbine efficiency can be improved by increasing the turbine inlet temperature. Secondary flows created in the turbine blade passage cause pressure losses and increase the thermal blade loading on the endwall, thus limiting the combustion temperature. Pressure losses, or aerodynamic losses, extr...
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| Format: | Others |
| Language: | en |
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LSU
2005
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| Online Access: | http://etd.lsu.edu/docs/available/etd-04142005-184449/ |