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- Type of Document: M.Sc. Thesis
- Language: Farsi
- Document No: 44278 (45)
- University: Sharif University of Technology
- Department: Aerospace Engineering
- Advisor(s): Mazaheri, Karim
- Abstract:
- Turbojet engine combustors play a key role to convert energy with very high rates. To reach this goal, the combustor must satisfy many conflicting requirements. Complexity of the flow field inside the combustormakes the 2D or 3D analysis very difficult. In this thesis, a quasi one-dimensional software is developed applying empirical and analytical 1D relations. Using data for a mini-turbojet engine, the range of some important design parameters is extracted and then a new combustor is designed using both velocity and pressure loss methods. Different disigns are investigated and are compared by employing an extended version of the simulation software. Due to the unacceptable performance indices such as high pressure loss and unsuitable flow distribution throghout the combustor, a differential evaluation algorithm is applied to optimize the design. In the optimization process, the combustor pressure loss is selected as a target function, and geometry of the holes and radial position of the liner were chosen as optimization variables. After optimization, the total pressure loss of the combustor is suprresed about 12% using velocity method and applying pressure loss method the decrease of the pressure loss is about 26%
- Keywords:
- Simulation ; Quasi One Dimensional ; Design ; Optimization ; Annular Combustor
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