FIELD: engines.
SUBSTANCE: gas turbine engine according to one illustrative aspect of this invention includes a reducer located along the longitudinal axis of the engine and a stage located along said longitudinal axis of the engine and activating the reducer, wherein said stage comprises a low pressure turbine with a small number of steps. In the following non-limiting example of one of said variants of gas turbine engine, the small number of steps may consist of three to six (3-6) steps. Additionally or alternatively, the small number of steps may be three (3) steps. Additionally or alternatively, the small number of steps may be five (5) or six (6) steps.
EFFECT: light and efficiently functioning engine design and ensured high flight efficiency.
15 cl, 15 dwg
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