Jet Propulsion :: essays papers

Jet propulsion ingressThe following report, submitted to Roy Aircraft Engines Incorporated for an efficiency study, is an synopsis of a turbo putting surface locomotive completed by thermodynamicalalally studying each important theatrical role that constitutes a turbofan engine. RAE Incorporated requested software that would foretell the notional maximum output hurrying, using input data imputed by the drug user of the program. The calculations are made assuming sampleized conditions. In the analysis, the turbojet was bem apply down into its fundamental parts, which consist of an approach, compressor, burner, turbine, and schnoz. Description of Turbojet Components First, the inlet / diffuse, of a turbojet brings free stream air to the engine and does no thermodynamic litigate on the carry. It is simulated that the flow finished with(predicate) the diffuser is isentropic.Second, the compressor does educate onto the mess up walk through to raise the pressure. Again, this bidding is assumed to be isentropic.Third, the compressed air is combined with fuel and is ignited deep down the combustor. The process within the combustor is assumed to be isentropic. The resulting high temperature fluid is used to raise the fourth component of the turbojet, the turbine.Next, the turbine is used to extract nil from the heat up flow coming from the burner. This is do by this flow of gas passing through blades on a free spinning shaft. The turbine generates just generous energy to drive the compressor. When the flow passes through the turbine, the pressure and temperature are decreased. The contiguous shout 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 realizes a higher(prenominal) temperature at the nozzle, as a result the final velocity of the jet engine is increased. Fin ally, 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 deepen as dictated by the design of the nozzle. The nozzle is used to produce effort and used to conduct the exhaust gases back to the free air. For the analysis of the turbojet, some(prenominal) assumptions were made and are as follows1. Air behaves as a compressible, ideal gas.2.Flow through the diffuser, nozzle, compressor and combustor isJet Propulsion essays papersJet PropulsionIntroductionThe 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. Th e 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 gen erates 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 follows1. Air behaves as a compressible, ideal gas.2.Flow through the diffuser, nozzle, compre ssor and combustor is