Finite Volume Based Numerical Investigation On The Effects Of Internal Cooling And Film Cooling On The Thermal Performance Of Gas Turbine Blades

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dc.contributor.authorShaker, Sufian Farid
dc.date.accessioned2018-06-06T07:14:39Z
dc.date.available2018-06-06T07:14:39Z
dc.date.issued2010-05
dc.description.abstractThe inlet temperature of modern gas turbine engines has been increased to achieve higher thermal efficiency and increased output. The blade surfaces including the leading edge, suction side and pressure side are exposed to the most extreme heat loads, and therefore, must be adequately cooled to maintain safety. This thesis presents steady computational predictions for a three-dimensional numerical investigation for different cooling arrangement of turbine blade model with both the internal cooling and combines cooling (film cooling) techniques. The computational predictions were achieved using FLUENT . The dimension and the airfoil shape are generated by GAMBIT similar to the actual McDonnell Douglas (A-4 Skyhawk) blade with the same scale. The unstructured Triangular Pave mesh is used for all the blade models. The material considered in the analysis is stainless steel alloy-AL 6XN which is highly resistant to temperature. Turbulence was represented using the k- ω shear-stress transport (SST) model, and the flow was assumed to have a freestream turbulence intensity of 10%. The heat transfer coefficient, total temperature distribution, static pressure and velocity vector was investigated. The CFD heat transfer coefficient predictions compared well with the previous work. The results showed that heat transfer coefficient was higher with film cooling compared to without film cooling. For all the cases, the temperature distributions over the blade surface are obtained and presented. From the results, the CFD simulation has predicted that the blade with three rows of film cooling holes in the suction side, three rows in the pressure side and two rows in the leading edge with enternal channel is the best in terms of cooling performance. Besides these cases, the effect of coolant injection pressure ratio on temperature distribution , was investigated. Results showed that the increase in , has led to reduction in the temperature and moreover the lateral spreading facilitated the best coolant layer. This CFD code is also capable of handling unsteady flows. The periodic model was employed to predict the unsteady flow behavior during operation by a twodimensional numerical investigation for details of film cooling blade at three rotational speeds of 1800, 2550 and 3000 rpm. Results showed that the temperature of the rotor blade decreased slightly with the increase in the rotation speed due to the effect of flow acceleration.en_US
dc.identifier.urihttp://hdl.handle.net/123456789/5686
dc.language.isoenen_US
dc.publisherUniversiti Sains Malaysiaen_US
dc.subjectThe effects of Internal cooling and film coolingen_US
dc.subjecton The thermal performance of gas Turbine bladesen_US
dc.titleFinite Volume Based Numerical Investigation On The Effects Of Internal Cooling And Film Cooling On The Thermal Performance Of Gas Turbine Bladesen_US
dc.typeThesisen_US
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