Jet Propulsion :: essays papers

Jet Propulsion Introduction: The following report, submitted to Roy Aircraft Engines Incorporated for an efficiency study, is an analysis of a turbojet engine completed by thermodynamically studying each main component that constitutes a turbojet engine. RAE Incorporated requested software that would calculate the theoretical maximum output velocity, using input data imputed by the user of the program. The calculations are made assuming idealized conditions. In the analysis, the turbojet was broken down into its fundamental parts, which consist of an inlet, compressor, burner, turbine, and nozzle. Description of Turbojet Components First, the inlet / diffuser, of a turbojet brings free stream air to the engine and does no thermodynamic work on the flow. It is assumed that the flow through the diffuser is isentropic. Second, the compressor does work onto the gas passing through to raise the pressure. Again, this process is assumed to be isentropic. Third, the compressed air is combined with fuel and is ignited within the combustor. The process within the combustor is assumed to be isentropic. The resulting high temperature fluid is used to turn the fourth component of the turbojet, the turbine. Next, the turbine is used to extract energy from the heated flow coming from the burner. This is done by this flow of gas passing through blades on a free spinning shaft. The turbine generates just enough energy to drive the compressor. When the flow passes through the turbine, the pressure and temperature are decreased. The next step is optional within the program. Here an afterburner is used to reheat the exiting gas from the turbine. This is done by injecting additional fuel into the gas exiting from the turbine. Igniting this mixture produces a higher temperature at the nozzle, as a result the final velocity of the jet engine is increased. Finally, the flow comes through the nozzle where no thermodynamic work is performed on the flow by the nozzle. The temperature remains constant through the nozzle while the pressure and velocity of the flow will change as dictated by the design of the nozzle. The nozzle is used to produce thrust and used to conduct the exhaust gases back to the free air. For the analysis of the turbojet, several assumptions were made and are as follows: 1. Air behaves as a compressible, ideal gas. 2. Flow through the diffuser, nozzle, compressor and combustor is Jet Propulsion :: essays papers Jet Propulsion Introduction: The following report, submitted to Roy Aircraft Engines Incorporated for an efficiency study, is an analysis of a turbojet engine completed by thermodynamically studying each main component that constitutes a turbojet engine. RAE Incorporated requested software that would calculate the theoretical maximum output velocity, using input data imputed by the user of the program. The calculations are made assuming idealized conditions. In the analysis, the turbojet was broken down into its fundamental parts, which consist of an inlet, compressor, burner, turbine, and nozzle. Description of Turbojet Components First, the inlet / diffuser, of a turbojet brings free stream air to the engine and does no thermodynamic work on the flow. It is assumed that the flow through the diffuser is isentropic. Second, the compressor does work onto the gas passing through to raise the pressure. Again, this process is assumed to be isentropic. Third, the compressed air is combined with fuel and is ignited within the combustor. The process within the combustor is assumed to be isentropic. The resulting high temperature fluid is used to turn the fourth component of the turbojet, the turbine. Next, the turbine is used to extract energy from the heated flow coming from the burner. This is done by this flow of gas passing through blades on a free spinning shaft. The turbine generates just enough energy to drive the compressor. When the flow passes through the turbine, the pressure and temperature are decreased. The next step is optional within the program. Here an afterburner is used to reheat the exiting gas from the turbine. This is done by injecting additional fuel into the gas exiting from the turbine. Igniting this mixture produces a higher temperature at the nozzle, as a result the final velocity of the jet engine is increased. Finally, the flow comes through the nozzle where no thermodynamic work is performed on the flow by the nozzle. The temperature remains constant through the nozzle while the pressure and velocity of the flow will change as dictated by the design of the nozzle. The nozzle is used to produce thrust and used to conduct the exhaust gases back to the free air. For the analysis of the turbojet, several assumptions were made and are as follows: 1. Air behaves as a compressible, ideal gas. 2. Flow through the diffuser, nozzle, compressor and combustor is