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Gas turbine note: The original publication is AEJG-report-2006-1.pdf, but at the time of writing this, it was unavailable and we used the 2nd edition as a replacement. This text has been edited to reflect that change. The following references have been made to the first edition, instead of second edition: In section 3.2, an older draft report is referenced alongside two later drafts; section 7 references a 2005 conference paper from 2005 instead of a 2009 conference paper from 2009 or later; and Section 12 references a conference paper from 2004 instead of a 2008 conference paper from 2008 or later. Gas turbines are used for various purposes in many industries. They can be used in mining, electricity production, transportation (ships, trains, aircraft), heavy construction (excavators, earthmoving), and stationary power generation. The following are the most notable configurations of the gas turbine engine. Individual components of each engine type will differ based on manufacturer design and application. A turbojet is an airbreathing jet engine, typically used in aircraft. Air is drawn into the rotating compressor via the intake and is compressed to a higher pressure before entering the combustion chamber via the front nozzle. The compressor incorporates a centrifugal fan that uses some of its energy to drive the compressor. The turbine section removes energy from the high pressure air and uses it to power the compressor. The majority of energy in the compressed air is used to drive the high-pressure (HP) compressor. The remainder of this air flows into a combustion chamber where it is mixed with fuel and ignited. Combustion of fuel generates a hot gas, which expands through a nozzle to provide thrust. A slat must be used to minimize the formation of shock waves, which reduce efficiency. After leaving the combustion chamber, the hot gas expands through a nozzle to produce thrust. The gas takes on a more linear shape with increased temperature, which is why hot air tends to rise. The expansion exhausts through an outlet nozzles positioned at the bottom of each wing or tail fin. The modern turboprop engine is a highly refined version of the original turbojet. A turboprop engine consists of an intake, a compression section, which includes a centrifugal compressor and a propulsive nozzle, and an expansion section. The exhaust gases exit through an exhaust mixer which is connected to the inlet of the centrifugal compressor. This closed circulation allows thrust to be maintained with very little net thrust produced by the engine (about 10% from memory). The use of a turbine to power the compressor adds weight and cost but allows for a smaller more efficient propeller that has less drag. In turn this increases fuel efficiency due to less energy required for net thrust production. cfa1e77820
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