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JET ENGINE THEORY AND DESIGN

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JET ENGINE THEORY AND DESIGN ( jet-engine-theory-and-design )

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Many engine designs now use combination disc and drum compressor rotor assemblies due to their split spool design concept. The F404-GE-402 and the F414-GE-400 are examples of the combination compressor rotor assembly. The coverage of axial-flow compressors up to this point has dealt solely with the conventional single-rotor type. Actually, there are two configurations of the axial compressor now in use, the single rotor and the dual rotor, sometimes referred to as solid spool (Figure 1-24) and split spool (Figure 1-25). One version of the solid-spool compressor uses variable inlet guide vanes. This is the arrangement found on the J79-GE-10 engine. The engine has a 17-stage compressor. The angles of the inlet guide vanes and the first six stages of the stator vanes are variable. During operation, air enters the front of the engine. Air is directed into the compressor at the proper angle by the variable inlet guide and variable stator vanes. The air is compressed and forced into the combustion section. A fuel nozzle extending into each combustion liner atomizes the fuel for combustion. These variables are controlled in direct relation with the amount of power the engine requires to produce the pilot’s power lever position. One version of the split-spool compressor is in General Electric’s F404 engine. It uses two compressors with their respective turbines and interconnecting shafts that form two independent rotor systems. The axial- flow type of engine has definite advantages. The advent of the split- spool axial compressor made these advantages even more positive by offering greater starting flexibility and improved high-altitude performance. Figure 1-23 — disc type compressor rotor. Figure 1-24 — Solid-spool compressor—single rotor turbine. Figure 1-25 — Split-spool compressor- dual rotor turbine. 1-16

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