Design and Fabrication Bi-fuel Gas Turbine Combustion Chamber Basis of Turbocharger

Azari Barzandigh, Fariborz | 2015

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 48251 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Farshchi, Mohammad; Hajilouy Benisi, Ali
  7. Abstract:
  8. This research is done as a continuation of previous efforts to develop a turbojet engine from a turbocharger at departments of mechanical and aerospace engineering of Sharif University of Technology and describes the necessary steps in order to design and build a dual fuel combustion chamber for a small, turbocharger based turbojet engine. At first, zero-dimensional analysis is done using a code written in Matlab. Using this code, matching of the compressor and turbine in the turbojet thermodynamic cycle is verified and the operating line of the turbojet engine has been extracted. Henceforth, operating conditions of the combustion chamber to start design process is determined. In designing the combustion chamber, after sizing the chamber using empirical correlations and determination of details using previous experience and available references, Fluent has been used to survey the cold flow field in the chamber which resulted in determination of the exact location of the spark plug. Finally, manufacturing drawings provided and the chamber was built. Providing necessary auxiliary systems like fuel system, ignition system, oil system and data logging, test bed was completed and experimental study on the engine started. The engine was successfully tested in the 45000 to 90000 range of RPM and the maximum extracted thrust was found to be 74 Newtons. When the speed became less than 45000 RPM, the engine could not operate in steady state due to low compressor pressure ratio along with low efficiency
  9. Keywords:
  10. Turbochargers ; Combustion Chamber ; Turbojet ; Zero-Dimensional Modeling ; Experimental Studies

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