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Analytical Solution of the Swirl Flow in Combustion Chamber of a Hybrid Rocket Engine

Mohammad Beiki, Shahab | 2017

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 49782 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Farahani, Mohammad; Rezayi, Hadi
  7. Abstract:
  8. Hybrid engines are one of a variety of chemical propulsion systems that have been given special attention in recent years by various industries such as space and defense. The most important reasons for considering this type of system are its high safety, its affordable price compared with liquid fuel propulsion systems, the possibility of switching on and off and changing thrust. This system has a lot of disadvantages as well. This system cannot meet all the needs of different industries due to the low regression rate and, consequently, the limitation of the operating range, thrusts and special impulse. As a result, increasing the fuel regression rate in these engines can greatly expand their use. In this study, a hybrid engine with solid fuel of polyethylene and the oxidizer of gas is used. This combination of fuel and oxidizer has been very much taken into account in recent years due to the advantages and characteristics of the polyethylene and that has self-compression properties, that required by the pump system, and in many hybrid engines it has been used. Fuel regression rate, is one of the most important parameters in hybrid rocket engines and the key parameter in designing these types of engines. Therefore, it is important to study the factors affecting the rate of regression and find ways to promote it. The main objective of this research is to investigate the effect of swirl flow injection of oxidizer in a combustion chamber on the regression rate of solid fuel. This is done by analyzing swirling flow in a cylindrical chamber, taking into account the corrosion and mass addition from the walls into the main flow - in order to consider the solid fuel regression. To do this, the flow function inside the chamber is first obtained and then calculating other flow characteristics such as velocity. By having these parameters, one can set the regression rate based on each parameter and obtain the regression rate. Finally, the data will be compared and validated with experiments and experimental data
  9. Keywords:
  10. Swirling Flow ; Performance Parameter ; Combustion Chamber ; Regression Analysis ; Hybrid Rocket ; Hot Test

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