FIELD: engines and pumps.
SUBSTANCE: proposed engine comprises first compressor furnished with blades arranged in its edges, combustion chamber 23 and first turbine provided with, at least, one row of turbine blades distributed over its edges. First compressor and first turbine ate rigidly coupled by rotary shaft. First turbine is adapted to act on normalised gas flow rate through gas turbine depending upon first turbine rpm. First turbine rotor is fitted directly downstream of combustion chamber to exclude nozzle blades or similar flow deflectors downstream of combustion chamber and upstream of turbine first rotor. Besides, gas turbine comprises first turbine rpm controller.
EFFECT: aircraft gas turbine with lower consumption of fuel.
33 cl, 7 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| COMPRESSOR CONTROL | 2018 |
|
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