Abstract:
Rocket engines are getting more popular day by day with the involvement of private companies in the space industry. Reusable rockets and lander vehicles are gaining more importance with the upcoming technologies regarding space exploration. Throttleable rocket engine is one of the key components for these rockets and vehicles. In this thesis, a 5 kN pressure fed and water cooled rocket engine was designed, manufactured and tested as a starting point for developing a throttleable and regeneratively cooled rocket engine. %75 concentrated ethanol-water mixture is used as the fuel and liquid oxygen is used as the oxidizer. Engine is designed to work at 30 bar chamber pressure for 1.01 kg/s and 1.26 kg/s fuel and oxidizer mass flow rates, respectively. A preliminary design procedure for the thrust chamber is explained. Cooling channel geometry, and heat transfer between the hot combustion gases and the coolant flow are investigated. Cavitating venturies are used for the mass flow rate control. Their designs and tests are discussed in detail. A test stand is developed to test the engine. Overview of the test stand and pressure control systems are explained. Engine firing test is conducted and achieved mass flow rates are found out to be lower than the expected. 0.89 kg/s fuel and 0.83 kg/s oxidizer mass flow rates are achieved at the final complete thrust chamber test. Possible causes for this situation are investigated.
