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PIONEERING THE POWER THAT MATTERS RR 2018 Gas turbine technology Introduction

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PIONEERING THE POWER THAT MATTERS RR 2018 Gas turbine technology Introduction ( pioneeringpower-that-matters-rr-2018-gas-turbine-technology- )

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10 Gas turbine technology Introduction to a jet engine The combustor Injecting the energy The annular combustion chamber is located within a casing structure. Kerosene is introduced through fuel injectors into the front of the chamber. Gas turbine technology 11 Introduction to a jet engine It burns fuel with air received from the compressor, sending hot gas downstream to the turbine. A typical in-service combustor is shown below. Air and fuel flow through the annular combustor. Air is diffused around the outside of the combustion chamber, slowing it down; the speed at which the air leaves the compressor would blow out the flame were it to pass directly through. In the illustration, blue shows the combustion feed air from the HP compressor, and white through yellow to red, the hot combustion gases in the burning zones being cooled before entering the turbine system. The gas temperatures within the combustor are above the melting point of the nickel alloy walls. Cooling air and thermal barrier coatings are therefore used to protect the walls and increase component lives. Dilution air is used to cool the gas stream before entering the turbines. The combustion chamber is designed for long life and low emissions. The turbine extracts energy from the hot gas stream received from the combustor. In a turbofan this power is used to drive the fan and compressor. Turbine blades convert the energy stored within the gas into kinetic energy. Like the compressor, the turbine comprises of a rotating disc with blades and static vanes, called nozzle guide vanes. The gas pressure and temperature both fall as it passes through the turbine. HP turbine blades and nozzle guide vanes are designed with cooling passages and thermal barrier coatings, to ensure long life while operating at such high temperatures. Cooling air is taken from the compressor and is fed around the combustor into the blades to cool the aerofoils. The turbine Harvesting the power The turbine is an assembly of discs with blades that are attached to the turbine shafts, nozzle guide vanes, casings and structures. IP turbine LP turbine HP turbine HP turbine blade HP turbine blade cooling flows Blade cooling air The melting point of the material in the combustion chamber is 1300°C, this is like taking a tray of ice from the freezer and putting it into a domestic oven at 300°C and keeping it frozen for up to 10 years. Fuel injector Igniter Secondary zone Nozzle guide vane Diffuser Primary zone Dilution zone Fuel is burned in the combustion chamber at temperatures of over 2000°C, about half the temperature of the sun.

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