FIELD: engines and pumps.
SUBSTANCE: aircraft engine comprises inlet device, compressor, countercurrent combustion chamber, jet nozzle and reduction gearbox. Gas turbine is arranged across engine axis. Combustion chamber is arranged in engine axis at the structure centre. Engine shaft should be designed for compression by gas forces produced in compressor. Note here that shaft length should be decreased by turbine length.
EFFECT: decreased weight and length of proposed engine.
3 dwg
Title |
Year |
Author |
Number |
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2013 |
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