Components And Systems Operations Of Turbine Enginesâ€Free Samples

Question: Discuss About The Components And Systems Operations Of Turbine Engines? Answer: Introducation A turbine engine comprises of several components and systems and this review intends to give a brief description of the various systems and their way of operation. The systems that make up a turbine engine are induction, fire detection systems, engine overheat, instrumentation, exhaust, cooling, charging, starting, electrical, lubrication, ignition, water injection, fuel metering, and fuel delivery (Anderson, 2009). The induction system is used to supply high energy, distortion free air to the compressor so as to prevent stalling of the compressor and maintain the internal temperature of the engine. It should also be capable of delivering most of the pressure recovered from the air to the engine with minimum loss of pressure. It can have a fixed or variable geometry. The turbines capability to deliver the required thrust depends on the ability of the fuel delivery system to vary the fuel flow to the combustion chamber. If the fuel is supplied in excess, then it results in rich blowout condition and if the supplied fuel is lower than the requirement then it results in lean die out condition both of which should be avoided (Anderson, 2009). Fuel pumps are used to deliver the required fuel for the operation of the engine at the desired pressure so as to obtain accurate nozzle spray and fuel regulation. They can be grouped into variable and constant displacement systems. A fuel heater is required to warm the fuel because residual water in the fuel tank freezes when the fuel in the tank cools to 32 C or lower. Thus protecting the fuel from ice formation. The fuel controllers are protected from contamination using a high pressure fuel filter (Anderson, 2009). Other control devices and fuel pump are protected using a low pressure filter installed between the fuel system and the supply tanks. Most commonly used filters are plain screen mesh filter, wafer screen filter and micron filter. Fuel flow meters are used to determine the fuel consumption; they are also used to know about the efficient operation of the engine. Fuel Nozzles are used to inject fuel into the combustion chamber in a precise and highly atomized manner so that the burning takes place in the smallest of space within the shortest time period (Anderson, 2009). If the fuel is not evenly distributed, then the flame may burn through the liners and create hot spots in the combustion chamber. Simplex and duplex configurations are two types of nozzles normally used. The fuel is divided into primary and main manifolds using the pressuring valves and the cut off provided by this valve prevents the fuel from dribbling into the manifold via the fuel nozzle (Anderson, 2009). Hydro-mechanical and electronic systems are the two basic groups of fuel control (Greatrix, 2012). The hydro-mechanical system consists of metering systems, feedback or follow-up devices, sleeve and pilot valves, servo systems, and speed governors (Greatrix, 2012). Whereas, electronic fuel control systems consist of solenoids, switches, electrical servo systems, relays, thermocouples, and amplifiers. Water injection systems are used to increase the engine thrust and to reduce the hot section temperature by injecting water into engine diffuser case and allows higher fuel flow through cooling principle. Ignition systems are used during the starting phase of an engine usually a capacitor type ignition system is used for igniting the fuel using a high heat intensity spark (Greatrix, 2012). It includes two high tension leads, two intermediate ignition leads, two transformers and two exciter units (Greatrix, 2012). Turbine engines used both wet and dry sump lubrication systems and is used to ensure proper temperatures are maintained (Greatrix, 2012). Bearings and gears are lubricated using pressure pumps and scavenge pumps are used to return the oil back to the oil tank. Oil jets mounted next to each bearing is also used to lubricate the bearings. Carbon seals are used to provide sealed areas for lubrication to take place. Oil coolers are used to cool down the oil after lubrication. Bleed air system is used to provide bleed air for compressor stability, cooling, clearance and other systems. Anti-ice system is used to provide protection against formation of ice in the inlet. A starter system is used to start the compressor so as to start the turbine engine using electric, air turbine or combustion starters (Kroes and Wild, 2010). Cooling system cools the engine by either passing a liquid coolant through the jacket surrounding the cylinder or by passing air over the fins attached to the cylinder (Kroes and Wild, 2010). Exhaust gas are released using as exhaust duct provided in the tailpipe or the exhaust pipe thereby connecting the jet nozzle to the outlet. The engine operations are controlled using the instrumentation cluster which include fire warning indicators, thrust reverser indication, power plant ice protection indication, vibration indication, engine starter indication, fuel heat indication, fuel filter impending bypass indication, oil filter bypass indic ation, air temperature indicator, fuel inlet pressure indicator, oil quality indicator, engine oil temperature indicator, engine oil pressure indicator, fuel flow indicator, exhaust gas temperature indicator, tachometer, torque meter and engine pressure ratio indicator (Kroes and Wild, 2010). References Anderson, K. (2009). Propulsion Plant Accident Investigation. Embry-Riddle Aeronautical University. Greatrix. D.R. (2012). Gas Turbine Engines: Fundamentals. In: Powered Flight. London: Springer Kroes, M.J. and Wild, T.W. (2010). Aircraft Powerplants (Aviation Technology Series). New Delhi, new Delhi: McGraw-Hill Higher Education.