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Aerodynamics Design of Aviation High-speed Radial Turbine with a Feasibility on Cooling

Zolfaghari Nasab Hajizadeh, Abolfazl | 2022

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 55576 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Ghorbanian, Kaveh
  7. Abstract:
  8. Radial turbines with small dimensions and in small power capacities are of great interest. In general, turbine performance improvement and higher output power may be achieved through increasing the inlet mass flow rates however at the expense of more weight and larger dimensions. On the other hand, increasing the inlet total temperature to the turbine will result in higher power potentials. Nevertheless, the turbine needs to be cooled in case that the intended inlet temperature goes beyond the turbine material limitation. In this thesis, radial turbine equations are reviewed and the logic of a 1D algorithm is developed where parameters like the total temperature, total pressure, and mass flow rate are used as an input to obtain the required geometrical, performance, and aerothermodynamics information. The developed algorithm is evaluated by comparing with experimental data available from public literature. Further, the results are also compared with 3D simulations. Once ensured of the accuracy of the developed algorithm, a specific uncooled radial turbine with a performance of interest is designed. The inlet flow temperature to this turbine is considered 1150 K and the pressure 450 kPa with inlet mass flow rate equals to 1.5 kg/s. The rotational speed is 40000 rpm. Finally, cooling methodologies are studied. The possibility of adopting nozzle cooling to the abovementioned radial turbine is examined for increasing the inlet total temperature to the values of 1500 and 1800 K while maintaining the geometry of the turbine rotor. The results are also confirmed by performing 3D simulations. The results indicate that the inlet total temperature to the cooled nozzle could not be increased without altering the rotor geometry
  9. Keywords:
  10. Aerodynamic Design ; One Dimentional Algorithm ; Nozzle Cooling ; Aviation Radial Turbine ; Feasibility Study ; Turbine Cooling

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