Gas Turbine Engine Basics Coursework Example | Topics and Well Written Essays - 2000 words - 1

Gas Turbine Engine Basics - Coursework ExampleAccording to relevant sources, a turbo-propeller plane engine is a turbine that drives a propeller via a reduction gear as shown in the above diagram (NASA 4). As such, the exhaust gases drive the military unit shaft, which in turn drives the reduction gear assembly through a shaft as shown (Husain 98 Sickle 205). The reduction gearing is essential because optimal propeller performances in these engine designs are reached at slower speeds than the engines operating revolution per minute. At slow airspeeds, these engine designs are fuel efficient and course effectively (FOPPGS 1).Turbofan engines were developed to incorporate some of the best features that exist in the already mentioned engines (FOPPGS 1). For example, these engines have been designed to generate additional thrust by directing a secondary airflow around the combustion chamber (NASA 4). Additionally, the bypass helps in cooling the engine, as well as helps in diminution exhaust noises. In a turbofan engine, therefore, the bypass ratio refers to the ratio of the bargain airflow passing through the fan divided by the mass airflow passing through the engine core (FOPPGS 2).However, part of the inlet airflow is not directed toward the compressor, combustor, and turbine, but is rather bypassed through a duct, which ends in a nozzle. Since air leaves the nozzle at a speed that is higher than the intake velocity, thrust is produced by nerve impulse exchange with the airframe. During the intake phase, the pressure, temperature and volume of the gases bear constant.The compressor is an arrangement of blades on a rotating disk, whose main function is to force air to flow into the engine as it reduces its volume and increases its pressure. Torque is required to change the momentum of the working fluid, forcing it to follow the curved surface of the blades. The work required to drive the compressor comes from the engine itself, by means of a shaft connectin g the compressor and the turbine.