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Numerical Investigation of the Effect of Cooling Layout Manufacturing Tolerances on the Thermal Field of a Nozzle Guide Vane

Bafandkar, Mohammad Reza | 2025

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 58053 (08)
  4. University: Sharif University of Technology
  5. Department: Mechanical Engineering
  6. Advisor(s): Farhanieh, Bijan; Karimi, Mohammad Sadegh
  7. Abstract:
  8. One way to increase the efficiency and improve the performance of a gas turbine is to increase the inlet gas temperature. On the other hand, the inlet temperature has an allowable operating range, and increasing it beyond the tolerance of the alloys used in turbine blades causes structural defects and significantly reduces the blade life. Therefore, to increase the blade life, various cooling methods such as internal and layer cooling are used. Considering the blade geometry and cooling paths, accuracy in the manufacturing process is doubly important in the production of these blades. The importance of this issue is that if the cooling channels produced are inconsistent with the design drawings, it will disrupt the cooling system and reduce the blade life. Therefore, in the present study, a study of manufacturing tolerance has been carried out by considering the geometry and position of the internal cooling channels of the three-dimensional blade of the C3X turbine in order to compare thermal parameters. First, assuming the existence of ten circular channels, modeling and simulation were performed with the aim of extracting basic data based on NASA experiments (as an indicator of cooling analysis). Then, in order to investigate the thermal and fluid effects, three main categories of diameter change, channel center displacement, and a combination of the first two categories were considered. The results of the simulations clearly showed that we do not see any noticeable changes in the pressure and velocity fields due to the constant boundary conditions. However, in the temperature and heat transfer coefficient fields, these changes and deviations from the basic model were noticeable. Finally, in order to investigate the performance of the cooling channels, the maximum temperature and temperature gradient were calculated and compared in 6 groups of geometric changes. The results clearly showed that in diameter changes of 10%, the largest increase in temperature gradient is 15.30%, and in the high limit of combined changes, the largest decrease in the maximum temperature gradient area is -13.40%, which indicates the most appropriate performance compared to other groups
  9. Keywords:
  10. Gas Turbines ; Turbine Cooling ; Heat Transfer ; c3x Turbine Blade ; Turbine Performance ; Gas Turbine Blades

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